Calculators Created by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore
https://www.linkedin.com/in/maiarutselvan-v-ba5533149/
302
Formulas Created
297
Formulas Verified
73
Across Categories

List of Calculators by Maiarutselvan V

Following is a combined list of all the calculators that have been created and verified by Maiarutselvan V. Maiarutselvan V has created 302 and verified 297 calculators across 73 different categories till date.
Verified Normal force coefficient
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Verified Rolling moment
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Verified Rolling moment coefficient
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Verified Velocity along pitch axis for small sideslip angle
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Verified Velocity along roll axis for small angle of attack
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13 More Aerodynamic Nomenclature Calculators
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Verified Power required at an altitude
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Verified Power required at an altitude for given power required at sea-level condition
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4 More Altitude Effects on Power Required and Available Calculators
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Verified Current gain of the amplifier in decibels
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41 More Amplifiers Calculators
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Verified Coefficient of drag over the flat under the freestream flow conditions
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Verified Drag force over the flat plate
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Verified Freestream Stanton number for flat plate
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Verified Insulated flat plate, the weak interaction
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Verified Local heat transfer over flat plate using Stanton number
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10 More Approximate Results Applied to Hypersonic Vehicles Calculators
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Verified Ratio of stagnation and static pressure
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5 More Basic Compressible Flow Calculators
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Basics (2)
Verified Mach Number
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Verified Stagnation Temperature
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5 More Basics Calculators
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Verified Exact pressure coefficient for blast wave theory
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5 More Blast-wave part 2 Calculators
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Verified Coefficient of friction for given frictional force
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Verified Frictional force
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5 More Bodies connected by a string - one hanging free, other lying on a rough inclined plane Calculators
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Verified Tension in the string
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3 More Bodies connected by a string - one hanging free, other lying on a smooth inclined plane Calculators
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Verified Acceleration of the system for given mass of body A
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Verified Acceleration of the system for given mass of body B
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Verified Frictional force on body B
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Verified Tension in the string for given mass of body A
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Verified Tension in the string for given mass of body B
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1 More Bodies connected by a string and lying on rough inclined planes Calculators
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Verified Angle of inclination of plane with body A
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Verified Angle of inclination of plane with body B
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2 More Bodies connected by a string and lying on smooth inclined planes Calculators
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Created Area of surface for average drag coefficient in boundary layer flows
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Created Average coefficient of drag for drag force in boundary layer flows
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Created Coefficient of drag for Blasius's solution in boundary layer flow
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Created Coefficient of drag for Reynold number in the laminar boundary layer flow
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Created Distance from leading edge for Blasius's solution in boundary layer flow
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Created Distance from leading edge in boundary layer flow
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Created Drag force for average drag coefficient in boundary layer flows
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Created Drag force on the plate in boundary layer flow
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Created Freestream velocity for local drag coefficient in boundary layer flows
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Created Length of the plate for Reynold number in the laminar boundary layer flow
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Created Local drag coefficient for shear stress in boundary layer flows
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Created Reynold number at the end of the plate
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Created Reynold number for drag coefficient in Blasius's solution of boundary layer flow
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Created Reynold number for drag force on the plate in boundary layer flow
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Created Shear stress at the boundary for turbulent boundary layer over a flat plate
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Created Shear stress for local drag coefficient in boundary layer flows
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Created Thickness of boundary layer for Blasius's solution in boundary layer flow
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Created Thickness of boundary layer in boundary layer flow
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Created Velocity of fluid for Reynold number in the laminar boundary layer flow
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Created Viscosity of liquid for drag force on the plate in boundary layer flow
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Created Width of the plate for drag force on the plate in boundary layer flow
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Verified Local heat-transfer rate calculation using Stanton number
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Verified local heat-transfer rate using Nusselt's number
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Verified local shear stress at the wall
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Verified Nusselt's number with Reynolds number, the Stanton number and Prandtl number
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Verified Prandtl number with Reynolds number, Nusselt's number, Stanton number and Stanton number
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Verified Stanton number for hypersonic vehicle
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Verified Static Density equation using skin friction coefficient
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Verified Static density equation using Stanton number
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Verified Static velocity equation using skin friction coefficient
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Verified Static velocity using Stanton number
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Verified Static viscosity relation using temperature of wall
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Verified Thermal conductivity at the edge of the boundary layer equation using Nusselt's number
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Verified viscosity around the wall
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7 More Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions Calculators
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Created Angle of heel for metacentric height in experimental method
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Created Centre of Buoyancy
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Created Meta-centric height for time period of oscillation and radius of gyration
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Created Meta-centric height in the experimental method
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Created Movable weight for metacentric height in experimental method
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Created Radius of gyration for metacentric height and time period of oscillation
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Created Time period of oscillation in the ship
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Created Volume of body in fluid for metacentric height and BG
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Created Volume of fluid displaced
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Created Absolute temperature for the velocity of sound wave in the isothermal process
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Created Absolute temperature for velocity of sound wave in terms of adiabatic process
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Created Bulk modulus for the velocity of sound wave
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Created Density of fluid considering velocity at outlet of orifice
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Created Density of the fluid for stagnation considering compressible fluid flow
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Created Mach angle for the compressible fluid flow
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Created Mach number for the compressible fluid flow
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Created Pressure at inlet considering maximum flow rate of fluid
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Created Pressure at inlet of the tank or vessel considering compressible fluid flow
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Created Pressure ratio for maximum flow rate through nozzle or orifice
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Created Stagnation density considering other stagnation properties of the fluid
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Created Stagnation density considering the compressible fluid flow
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Created Stagnation pressure considering other stagnation properties of the fluid
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Created Stagnation pressure for the compressible fluid flow
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Created Stagnation temperature considering other stagnation properties of the fluid
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Created Stagnation temperature considering the compressible fluid flow
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Created Temperature of fluid for stagnation temperature considering compressible fluid flow
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Created Velocity at the outlet of the nozzle for maximum flow rate of fluid
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Created Velocity of fluid considering the Mach angle in the compressible fluid flow
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Created Velocity of sound wave considering Mach angle in the compressible fluid flow
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Created Velocity of sound wave in Mach number for the compressible fluid flow
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Created Velocity of sound wave in terms of an adiabatic process
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Created Velocity of sound wave in terms of bulk modulus
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Created Velocity of sound wave in terms of isothermal process
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Verified Emissivity
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Verified Reference viscosity
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2 More COMPUTATIONAL-FLUID-DYNAMIC SOLUTIONS Calculators
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Verified Sideslip angle
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Verified Vertical tail angle of attack for given vertical tail side force
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Verified Vertical tail area for given vertical tail side force
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Verified Vertical tail dynamic pressure for given vertical tail side force
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Verified Vertical tail lift curve slope
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Verified Vertical tail lift curve slope for given moment
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Verified Vertical tail Side force
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8 More Contribution of Aircraft Components (Part 1) Calculators
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Verified Sideslip angle for given yawing moment coefficient
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Verified Sidewash angle for given moment produced by vertical tail
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Verified Vertical tail dynamic pressure for given moment
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Verified Wing area for given moment produced by vertical tail
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Verified Wing dynamic pressure for given yawing moment coefficient
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Verified Wingspan for given yawing moment coefficient
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8 More Contribution of Aircraft Components (Part 2) Calculators
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Verified Dynamic pressure at wing for given yawing moment coefficient
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Verified Vertical tail efficiency for given yawing moment coefficient
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Verified Vertical tail lift curve slope for given yawing moment coefficient
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Verified Wingspan for given yawing moment coefficient
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Verified Yawing moment coefficient for given vertical tail volume ratio
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10 More Contribution of Aircraft Components (Part 3) Calculators
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Verified Sideslip angle for given yawing moment coefficient
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Verified Sidewash angle for given yawing moment coefficient
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Verified Convection resistance for a cylindrical layer
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Verified Length of the cylindrical wall for a given heat flow rate
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Verified Thickness of the cylindrical wall to maintain a given temperature difference
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11 More Cylinders Calculators
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Verified Zero-lift drag coefficient at minimum required thrust
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Verified Zero-lift drag coefficient for given required thrust
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5 More Drag during Level Unaccelerated Flight Calculators
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Created Actual discharge in venturimeter
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Created Coefficient of pitot-tube for velocity at any point
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Created Difference in pressure head for heavier liquid in manometer
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Created Difference in pressure head for light liquid in manometer
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Created Resultant force on bend for force along x and y-direction
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Created Velocity at any point for coefficient of pitot-tube
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Verified Emissivity per unit mole
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Verified Kinetic energy per mole
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Verified Kinetic energy per mole using molar volume
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Verified Kinetic energy per mole using temperature of gas
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Verified Mean free path of a single-species gas,
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Verified Pressure using kinetic energy per mole
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Verified Pressure using molar volume
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Verified Specific gas constant using kinetic energy per mole
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Verified Temperature of gas using Emissivity per unit mole
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Verified Temperature of gas using kinetic energy per mole
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5 More ELEMENTS OF KINETIC THEORY Calculators
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Verified Elevator area for given hinge moment coefficient
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Verified Elevator Hinge moment coefficient
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Verified Elevator Hinge moment for given hinge moment coefficient
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2 More Elevator Hinge Moment Calculators
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Verified Coefficient of friction using Stanton number for flat plat case
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Verified Drag per unit span
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Verified Prandtl number for flat plate viscous flow
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Verified Recovery Factor using temperature
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Verified Skin-friction drag for flat plate in viscous flow
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Verified Stanton number using aerodynamic heating equation
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Verified Static density equation using aerodynamic equation
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Verified Static velocity equation using aerodynamic heating equation
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7 More Flat-Plate for Viscous flow case Calculators
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Verified Load factor for a given turn radius for a high-performance fighter aircraft
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Verified Turn radius for a high load factor
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Verified Turn rate for a given lift coefficient
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Verified Velocity for a given turn radius for a high load factor
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11 More Flight Envelope Calculators
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Created Area of flow for a circular channel
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Created Bazin's constant
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Created Chezy's constant considering Bazin formula
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Created Chezy's constant considering Kutter's formula
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Created Chezy's constant considering Manning's formula
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Created Chezy's constant considering velocity
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Created Critical depth considering flow in open channels
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Created Critical depth considering minimum specific energy
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Created Critical depth considering the critical velocity
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Created Critical velocity considering flow in open channels
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Created Discharge per unit width considering flow in open channels
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Created Hydraulic mean depth considering Bazin formula
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Created Hydraulic mean depth considering Manning's formula
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Created Hydraulic mean depth using Chezy's formula
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Created Manning's coefficient or constant
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Created Minimum specific energy considering the critical depth
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Created Radius of a circular channel considering wetted perimeter
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Created Velocity of Chezy's formula
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Created Wetted perimeter for a circular channel
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Created Area of the nozzle at outlet for maximum power transmission through nozzle
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Created Area of the pipe for maximum power transmission through nozzle
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Created Coefficient of contraction for sudden contraction
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Created Diameter of nozzle for maximum power transmission through nozzle
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Created Diameter of the equivalent pipe
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Created Difference in liquid level in three compound pipes with same friction coefficient
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Created Discharge in the equivalent pipe
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Created Efficiency of power transmission in flow through pipes
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Created Efficiency of power transmission through nozzle for velocity and total head
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Created Efficiency of power transmission through the nozzle
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Created Head available at the base of the nozzle
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Created Head loss due to friction for the efficiency of power transmission
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Created Intensity of pressure wave produced for gradual closure of valves
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Created Length of pipe for maximum power transmission through nozzle
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Created Length of the equivalent pipe
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Created Loss of head at the entrance of a pipe
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Created Loss of head at the exit of pipe
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Created Loss of head due to bead in a pipe
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Created Loss of head due to obstruction in a pipe
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Created Loss of head due to sudden contraction
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Created Loss of head due to sudden enlargement
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Created Loss of head in the equivalent pipe
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Created Maximum area of obstruction in the pipe
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Created Power lost due to sudden enlargement
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Created Power transmission through pipes
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Created Retarding force for gradual closure of valves
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Created Time required to close the valve for gradual closure of valves
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Created Time taken by pressure wave to travel
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Created Total head at the inlet of pipe for head available at the base of the nozzle
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Created Total head available at inlet of pipe for efficiency of power transmission
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Created Velocity at section 1-1 for sudden enlargement
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Created Velocity at section 2-2 for sudden contraction
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Created Velocity at section 2-2 for sudden enlargement
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Created Velocity at the outlet for head loss at the exit of pipe
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Created Velocity of flow at the outlet of the nozzle
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Created Velocity of flow at the outlet of the nozzle for efficiency and head
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Created Velocity of fluid for head loss due to obstruction in a pipe
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Created Velocity of fluid in pipe for head loss at the entrance of a pipe
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Created Velocity of liquid at vena-contracta
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Verified Friction Coefficient
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Created Angle of attack for circulation developed on the airfoil
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Created Angle of attack for lift coefficient on the airfoil
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Created Area of the body for lift force in a body moving on a fluid
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Created Chord length for circulation developed on the airfoil
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Created Circulation developed on the airfoil
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Created Circulation for a single stagnation point
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Created Circulation for lift force on a cylinder
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Created Circulation in the location of stagnation points
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Created Coefficient of drag for sphere in Oseen formula when Reynolds number is between 0.2 and 5
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Created Coefficient of drag for sphere in stoke's law when Reynolds number is less than 0.2
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Created Coefficient of lift for an airfoil
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Created Drag force for a body moving in a fluid of certain density
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Created Freestream velocity for a single stagnation point
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Created Freestream velocity for lift coefficient in a rotating cylinder with circulation
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Created Freestream velocity for lift coefficient with tangential speed
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Created Length of the cylinder for lift force on a cylinder
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Created Lift coefficient for a rotating cylinder with circulation
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Created Lift coefficient for a rotating cylinder with tangential speed
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Created lift coefficient for lift force in a body moving on a fluid
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Created Lift force for a body moving in a fluid of certain density
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Created Lift force on a cylinder for circulation
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Created Location of stagnation points for a rotating cylinder in a uniform flow field
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Created Pressure drag from total drag force on a sphere
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Created Radius of cylinder for lift coefficient in a rotating cylinder with circulation
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Created Radius of the cylinder for a single stagnation point
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Created Radius of the cylinder for location of stagnation points
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Created Skin friction drag from total drag force on a sphere
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Created Tangential velocity for a single stagnation point
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Created Tangential velocity of the cylinder with the lift coefficient
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Created Total drag force on a sphere
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Created Velocity of airfoil for circulation developed on the airfoil
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Verified 2-D Lift coefficient for cylinder
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Verified Airspeed measurement by venturi
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Verified Dynamic pressure in incompressible flow
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Verified Freestream density by Kutta-Joukowski theorem
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Verified Freestream velocity by Kutta-Joukowski theorem
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Verified Pressure difference measured by manometer in the low-speed wind tunnel
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Verified Radial velocity for 2-D incompressible source flow
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Verified Stream function for 2-D Doublet flow
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Verified Stream function for 2-D Vortex flow
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Verified Stream function for lifting flow over a circular cylinder
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Verified Stream function for semi-infinite body
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Verified Stream function for uniform incompressible flow
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Verified Tangential velocity for non-lifting flow over circular cylinder
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Verified Test section velocity for low sped wind tunnel in terms of height difference of manometric fluid
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Verified Test section velocity in low-speed wind tunnel
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Verified Total pressure in incompressible flow
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31 More Fundamentals of Inviscid Incompressible flow Calculators
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Created Feed force
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Created Radial force
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Created Side cutting edge angle for orthogonal cutting
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Created Side rake angle for orthogonal cutting
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6 More Geometry of Turning Process Calculators
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Verified Glide angle for given lift-to-drag ratio
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4 More Gliding Flight Calculators
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Verified Energy for the blast wave
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Verified Radial coordinate of blunt slab blast wave
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Verified Simplified pressure ratio for blunt cylinder blast wave
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Verified Time required for the blast wave
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12 More Hypersonic Equivalence Principle and Blast-Wave Theory Calculators
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Verified Pressure ratio of Blunt-nosed cylinder (first approximation):
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Verified Radial coordinate of Blunt-nosed cylinder (first approximation):
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Verified Radius for the cylinder-wedge body shape
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Verified Radius for the sphere-cone body shape
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5 More Hypersonic Flight Paths: Velocity-Altitude Map Calculators
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Verified Coefficient of pressure with similarity parameters
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Verified Mach ratio at high mach number
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Verified Pressure ratio for high Mach number
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Verified Pressure ratio having high mach number with similarity constant
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Verified Supersonic expression for pressure coefficient on a surface with local deflection angle θ
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15 More Hypersonic Flow Calculators
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Verified Non-dimensional pressure
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Verified Non-dimensional pressure for high mach number
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Verified Slenderness ratio with cone radius for hypersonic vehicle
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9 More Hypersonic Inviscid Flowfields: Approximate Methods Calculators
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Verified Detachment distance of cylinder-wedge
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Verified Detachment distance of sphere cone
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Verified Grid point calculation for shock waves
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Verified Nose radius of cylinder-wedge
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Verified Nose radius of sphere cone
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Verified Pressure ratio for unsteady waves
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Verified Ratio of new and old temperature
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11 More Hypersonic Inviscid Flowfields: Exact Methods Calculators
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Verified Change in velocity for hypersonic flow in x direction
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Verified Coefficient of pressure with slenderness ratio and similarity constant
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Verified Constant g used for finding the location of perturbed shock
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Verified Density ratio with similarity constant having slenderness ratio
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Verified Distance from tip of the leading edge to the base
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Verified Inverse of density for hypersonic flow using mach number
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Verified Non- dimensionalised time
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10 More Hypersonic Small-Disturbance Equations Calculators
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Verified Boundary-layer momentum thickness using Reynolds number at transition point
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Verified Eddy viscosity calculation
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Verified Local Mach Number using Reynolds number equation at transition region
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Verified Location of the transition point
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Verified Prandtl number of the transition flow
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Verified Specific heat at constant pressure for transient flow
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Verified Static density at transition point
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Verified Static density equation using boundary-layer momentum thickness
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Verified Static velocity at transition point
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Verified Static velocity using boundary-layer momentum thickness
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Verified Static viscosity at transition point
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Verified Static viscosity equation using boundary-layer momentum thickness
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Verified Transition Reynolds number
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3 More Hypersonic Transition Calculators
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Verified Large Mach number over a flat plate using static temperature and wall temperature
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Verified Pressure ratio for cold-wall case the strong interaction
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Verified Pressure ratio for cold-wall case the weak interaction
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Verified Static density of fluid over the flat plate
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Verified Static temperature over a flat plate using Static Mach Number
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Verified Static viscosity using wall temperature and static temperature
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Verified viscosity of wall using wall temperature and static temperature
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Verified Wall density of fluid over the flat plate
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Verified Wall temperature over a flat plate using Static Mach Number
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9 More Hypersonic Viscous Interactions Calculators
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Created Dimensions of Rankine half-body
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Created Distance between source or sink from origin
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Created Distance of stagnation point S from source in flow past a half body
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Created Location of stagnation point on x-axis
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Created Radial velocity at any radius
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Created Radius at any point considering radial velocity
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Created Radius of the Rankine circle
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Created Stream function at a point
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Created Stream function at a point in the combined flow
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Created Stream function in sink flow for angle
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Created Strength of doublet for stream function
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Created Strength of source for radial velocity and at any radius
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Created Strength of source for Rankine half body
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Created Uniform flow velocity for Rankine half body
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Created Uniform flow velocity for stream function at a point in the combined flow
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Verified Boundary layer thickness for laminar flow
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Verified Lift coefficient for cambered airfoil
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Verified Moment coefficient about leading-edge for symmetrical airfoil by thin airfoil theory
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5 More Incompressible flow over airfoil Calculators
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Created Angular velocity considering the depth of parabola
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Created Depth of parabola formed at the free surface of water
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Created Height or depth of paraboloid for volume of air
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Created Rate of flow or discharge
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Created Resultant velocity for two velocity components
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Created Total pressure force at the bottom of the cylinder
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Created Total pressure force on top of the cylinder
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Verified Dynamic pressure
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Verified Newtonian pressure distribution over the surface using cosine angle
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Verified Nusselt number at the stagnation point
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Verified Nusselt number for stagnation point on blunt body
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Verified Stagnation pressure
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2 More Laminar boundary layer at a stagnation point on a blunt body, Calculators
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Verified Touchdown velocity
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4 More Landing Performance Calculators
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Verified Lift-to-drag ratio for given required thrust
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Verified Thrust required for given Lift-to-drag ratio
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Verified Weight of aircraft for given Lift-to-drag ratio
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Verified Load factor for a given pull-down maneuver radius
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Verified Load factor for a given pull-up maneuver rate
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Verified Pull-down maneuver radius
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Verified Pull-up maneuver rate
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Verified Velocity for a given pull-down maneuver rate
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Verified Velocity for a given pull-up maneuver radius
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Verified Velocity for a given pull-up maneuver rate
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5 More Maneuvering Flight Calculators
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Created Cutting force for frictional force along the tool rake face, thrust force and normal rake angle
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Created Cutting force for given force along the shear force, thrust force, and shear angle
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Created Force along shear force for given force normal to shear force, shear, friction & normal rake angles
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Created Force along the shear force for given cutting force, thrust force, and shear angle
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Created Force normal to shear force for given cutting force, thrust force, and shear angle
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Created Frictional force along tool rake face for given cutting & thrust forces and normal rake angle
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Created Thrust force for given cutting force, shear angle & force along the shear force
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Created Thrust force for given cutting force, shear angle & force normal to shear force
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30 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
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Verified Coefficient of drag equation with coefficient of normal force
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Verified exact normal shock-wave maximum coefficient of pressure
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Verified Force F exerted on the surface
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Verified Mass flux incident on a surface area
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Verified Maximum Pressure coefficient
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9 More Newtonian Flow Calculators
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Verified Density behind normal shock for given upstream density and Mach number
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Verified Static enthalpy behind normal shock for given upstream enthalpy and Mach number
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Verified Static enthalpy ratio across a normal shock
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Verified Static pressure behind normal shock for given upstream pressure and Mach number
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Verified Static temperature behind normal shock for given upstream temperature and Mach number
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Verified Temperature ratio across a normal shock
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23 More Normal Shock Waves Calculators
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Created Coefficient of discharge for time required to empty a reservoir
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Created Discharge over a broad-crested weir
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Created Discharge over a broad-crested weir for head of liquid at middle
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Created Discharge over a broad-crested weir with velocity approach
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Created Discharge over a trapezoidal notch or weir
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Created Discharge over a triangular notch or weir
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Created Discharge over rectangle notch or weir
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Created Discharge over rectangle weir considering Bazin's formula
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Created Discharge over rectangle weir considering Francis's formula
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Created Discharge over rectangle weir for Bazin's formula with velocity approach
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Created Discharge over rectangle weir with two end contractions
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Created Discharge with velocity of approach
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Created Discharge without velocity of approach
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Created Head of liquid above the V-notch
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Created Head of liquid over the crest
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Created Length of crest of the weir or notch
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Created Length of section for discharge over rectangle notch or weir
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Created Length of weir considering Bazin's formula with velocity approach
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Created Length of weir considering Bazin's formula without velocity approach
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Created Length of weir considering Francis's formula
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Created Length of weir for broad-crested weir and head of liquid at middle
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Created Length of weir for broad-crested weir with velocity approach
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Created Length of weir for Discharge over a broad-crested weir
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Created Length of weir or notch for velocity of approach
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Created Length of weir or notch without velocity of approach
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Created Time required to empty a reservoir
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Created Time required to empty a tank with a triangular weir or notch
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Verified Component of downstream Mach no. normal to oblique shock for given normal upstream Mach no.
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Verified Density behind oblique shock for given upstream density & normal upstream Mach no.
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Verified Density ratio across the oblique shock
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Verified Flow deflection angle in terms of Prandtl Meyer function
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Verified Forward Mach angle of expansion fan
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Verified Pressure behind oblique shock for given upstream pressure & normal upstream Mach no
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Verified Pressure ratio across the expansion fan
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Verified Pressure ratio across the oblique shock
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Verified Temperature behind oblique shock for given upstream temperature & normal upstream Mach no.
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Verified Temperature ratio across the expansion fan
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Verified Temperature ratio across the oblique shock
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8 More Oblique Shock and Expansion Waves Calculators
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Verified Parallel upstream flow components after shock as Mach tends to infinite
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Verified Perpendicular upstream flow components behind the shock wave
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13 More oblique shock relation Calculators
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Created Absolute pressure head at constant head and atmospheric pressure head
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Created Area at vena contracta for discharge and constant head
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Created Area of mouthpiece In Borda's mouthpiece running free
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Created Area of mouthpiece In Borda's mouthpiece running full
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Created Area of orifice considering time of emptying a hemispherical tank
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Created Area of tank while considering time for emptying a tank
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Created Atmospheric pressure head at constant head and absolute pressure head
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Created Co-efficient of contraction
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Created Co-efficient of discharge
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Created Co-efficient of discharge considering time for emptying a tank
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Created Co-efficient of discharge considering time of emptying a circular horizontal tank
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Created Co-efficient of discharge considering time of emptying a hemispherical tank
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Created Co-efficient of discharge for area and velocity
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Created Co-efficient of velocity
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Created Co-efficient of velocity for horizontal and vertical distance
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Created Co-efficient of velocity for the head of liquid and head loss
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Created Discharge In Borda's mouthpiece running free
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Created Discharge In Borda's mouthpiece running full
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Created Discharge in the convergent-divergent mouthpiece
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Created Discharge through fully sub-merged orifice
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Created Discharge through large rectangular orifice
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Created Discharge through partially sub-merged orifice
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Created Head of liquid for head loss and coefficient of velocity
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Created Head of the liquid above the centre of orifice
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Created Horizontal distance for co-efficient of velocity and vertical distance
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Created Loss of head due to fluid resistance
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Created Loss of head due to sudden enlargement
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Created Theoretical velocity
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Created Time of emptying a circular horizontal tank
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Created Time of emptying a hemispherical tank
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Created Time of emptying a tank through an orifice at bottom
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Created Velocity of liquid at C-C for Hc, Ha, and H
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Created Vertical distance for co-efficient of velocity and horizontal distance
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Verified Area of a composite wall of 2 layers
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Verified Area of a composite wall of 3 layers
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Verified Inner surface temperature of a composite wall of 2 layers in series
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Verified Inner surface temperature of a composite wall of 3 layers in series
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Verified Inner surface temperature of a plane wall
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Verified Length of the 3rd layer of the composite wall for a given temperature difference
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Verified Temperature at distance x from the inner surface in the wall
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Verified Thermal resistance of a composite wall with 2 layers in series
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Verified Thermal resistance of a composite wall with 3 layers in series
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Verified Thermal Resistance of a wall
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12 More Plane walls Calculators
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Verified Power available for reciprocating engine-propeller combination
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Verified Propeller efficiency for reciprocating engine-propeller combination
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1 More Power Available and Maximum Velocity Calculators
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Verified Power required for given total drag
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Verified Total drag for given required power
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8 More Power Required for Level Unaccelerated Flight Calculators
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Verified Endurance of Propeller-Driven Airplane
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Verified Propeller Efficiency for given Endurance of Propeller-Driven Airplane
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Verified Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane
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Verified Propeller Efficiency for given Range of Propeller-Driven Airplane
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Verified Range of Propeller-Driven Airplane
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Verified Range of Propeller-Driven Airplane for given lift-to-drag ratio
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Verified Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
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Verified Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane
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Verified Specific Fuel Consumption for given Range of Propeller-Driven Airplane
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1 More Range and Endurance of Propeller-Driven Airplane Calculators
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Verified Thrust available for given excess power
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9 More Rate of Climb Calculators
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Verified Chord length for flat plate case
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Verified Local Reynolds number
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Verified local skin-friction coefficient
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Verified Mach number at reference temperature
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Verified Overall skin-friction drag coefficient for incompressible flow
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Verified Reference temperature equation
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Verified Stanton Number obtained from classical theory
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Verified Static viscosity of the plate using chord length for flat plate case
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Verified Wall temperature using the reference temperature
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7 More Reference Temperature Method Calculators
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Verified Elevator area for given stick force
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Verified Flight velocity for given stick force
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Verified Gearing ratio
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Verified Gearing ratio for given hinge moment coefficient
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Verified Hinge moment for given gearing ratio
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Verified Hinge moment for given stick force
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Verified Stick deflection angle for given stick force
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Verified Stick length for given stick force
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10 More Relationship between Stick Force and Hinge Moment Calculators
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Verified Dihedral angle for given sideslip velocity
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Verified Forward velocity for given normal component of side velocity
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Verified Normal component of side velocity for given dihedral angle
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Verified Normal component of side velocity for given forward velocity
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Verified Sideslip velocity for given dihedral angle
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Verified Coefficient of pressure equation using specific heat ratio
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Verified curvilinear grid location equation
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Verified Density equation using enthalpy and pressure
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Verified Enthalpy equation using pressure and density
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Verified pressure equation using Enthalpy and density
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6 More Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations Calculators
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Verified Convection resistance for a spherical layer
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Verified Heat flow rate through a spherical composite wall of 2 layers in series
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Verified Inner surface temperature of a spherical wall
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Verified Outer surface temperature of a spherical wall
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Verified Thermal resistance of a spherical composite wall of 2 layers in series with convection
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Verified Thickness of the spherical wall to maintain given temperature difference
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Verified Total thermal resistance of a spherical wall of 2 layers without convection
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Verified Total thermal resistance of a spherical wall of 3 layers without convection
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Verified Total thermal resistance of a spherical wall with convection on either side
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2 More Spheres Calculators
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Verified Angle of incidence of tail
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Verified Lift due to tail only
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Verified Lift due to wing only
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Verified Tail area for given tail efficiency
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Verified Tail Efficiency for given lift coefficients
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Verified Tail lift coefficient for given pitching moment
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Verified Tail Lift Coefficient of wing-tail combination
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Verified Tail lift for given tail pitching moment
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Verified Tail Pitching moment coefficient
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Verified Tail Pitching moment for given lift coefficient
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Verified Total Lift of wing-tail combination
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Verified Wing Lift Coefficient of wing-tail combination
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9 More Tail Contribution Calculators
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Verified Tail area for given tail moment coefficient
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Verified Tail Efficiency for given pitching moment coefficient
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Verified Tail lift coefficient for given pitching moment coefficient
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Verified Tail moment arm for given tail moment coefficient
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Verified Tail Pitching moment coefficient for given tail efficiency
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9 More Tail Contribution (Contd.) Calculators
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Verified Liftoff velocity for given weight
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13 More Takeoff Performance Calculators
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Verified Coefficient of Lift for given thrust and weight
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Verified Lift coefficient for given minimum required thrust
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Verified Minimum Thrust required for given lift coefficient
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Verified Thrust for given coefficients of lift and drag
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Verified Weight of aircraft for given coefficients of lift and drag
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7 More Thrust Required for Level Unaccelerated Flight Calculators
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Created Average height of irregularities for turbulent flow in pipes
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Created Discharge through pipe for power required and head loss in turbulent flow
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Created Head loss due to friction for power required and discharge in turbulent flow
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Created Power required to maintain the turbulent flow
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Created Roughness Reynold number for turbulent flow in pipes
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Created Shear stress developed for turbulent flow in pipes
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Created Shear velocity for turbulent flow in pipes
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Created Angular speed of outer cylinder in rotating cylinder method
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Created Buoyant force in falling sphere resistance method
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Created Density of fluid in falling sphere resistance method
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Created Diameter of capillary tube
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Created Diameter of pipe for difference in pressure in viscous flow
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Created Diameter of pipe for head loss due to friction in viscous flow
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Created Diameter of pipe for loss of pressure head in viscous flow
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Created Diameter of shaft for speed and shear stress of fluid in journal bearing
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Created Diameter of sphere in falling sphere resistance method
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Created Difference of pressure for viscous flow between two parallel plates
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Created Difference of pressure for viscous or laminar flow
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Created Discharge in capillary tube method
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Created Drag force in falling sphere resistance method
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Created External or outer radius of collar for total torque
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Created Internal or inner radius of collar for total torque
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Created Length for difference of pressure in viscous flow between two parallel plates
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Created Length for pressure head loss in viscous flow between two parallel plates
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Created Length of pipe for difference of pressure in viscous flow
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Created Length of pipe for head loss due to friction in viscous flow
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Created Length of pipe for loss of pressure head in viscous flow
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Created Length of tube in capillary tube method
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Created Loss of head due to friction
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Created Loss of pressure head for viscous flow between two parallel plates
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Created Loss of pressure head for viscous flow through circular pipe
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Created Maximum velocity at any radius with a velocity, and radius of pipe
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Created Power absorbed in collar bearing
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Created Power absorbed in foot-step bearing
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Created Power absorbed in overcoming viscous resistance in journal bearing
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Created Radius of pipe from maximum velocity and velocity at any radius
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Created Radius of shaft for torque required in foot-step bearing
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Created Rotational speed considering power absorbed and torque in journal bearing
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Created Rotational speed for torque required in collar bearing
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Created Rotational speed for torque required in foot-step bearing
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Created Shear force for torque and diameter of shaft in journal bearing
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Created Shear force or viscous resistance in journal bearing
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Created Shear stress in the fluid or oil of journal bearing
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Created Speed of rotation for shear force in journal bearing
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Created Thickness of oil film for shear force in journal bearing
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Created Thickness of oil film for speed and diameter of shaft in journal bearing
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Created Thickness of oil film for torque required in foot-step bearing
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Created Torque required considering power absorbed in journal bearing
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Created Torque required to overcome the shear force in journal bearing
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Created Torque required to overcome viscous resistance in collar bearing
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Created Torque required to overcome viscous resistance in foot-step bearing
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Created Total torque measured by strain in rotating cylinder method
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Created Velocity at any radius, radius of pipe, and maximum velocity
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Created Velocity of piston or body for movement of piston in dash-pot
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Created Velocity of sphere in falling sphere resistance method
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Created Viscosity of fluid or oil for capillary tube method
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Created Viscosity of fluid or oil for movement of piston in dash-pot
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Created Viscosity of fluid or oil in falling sphere resistance method
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Created Viscosity of fluid or oil in rotating cylinder method
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Verified Aerodynamic heating to the surface
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Verified Chapman–Rubesin factor
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Verified Coefficient of friction using Stanton equation for incompressible flow
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Verified Density calculation using Chapman–Rubesin factor
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Verified Stanton number for incompressible flow
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Verified Static Density calculation using Chapman–Rubesin factor
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Verified Static viscosity calculation using Chapman–Rubesin factor
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Verified Thermal conductivity using Prandtl number
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Verified Viscosity calculation using Chapman–Rubesin factor
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7 More Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating Calculators
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