Calculators Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu
https://www.linkedin.com/in/sanjay-krishna-80a7b913b/
301
Formulas Created
212
Formulas Verified
75
Across Categories

List of Calculators by Sanjay Krishna

Following is a combined list of all the calculators that have been created and verified by Sanjay Krishna. Sanjay Krishna has created 301 and verified 212 calculators across 75 different categories till date.
Verified Velocity along roll axis for small sideslip angle
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Verified Velocity along yaw axis for small angle of attack
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Verified Yawing moment
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Verified Yawing moment coefficient
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14 More Aerodynamic Nomenclature Calculators
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Verified Velocity at an altitude
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5 More Altitude Effects on Power Required and Available Calculators
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Created Adiabatic wall enthalpy over flat plate using Stanton number
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Created Coefficient of drag over the flat under the freestream flow conditions
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Created Drag force over the flat plate
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Created Free stream enthalpy over a flat plate with freestream conditions
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Created Free stream velocity over a flat plate using drag force
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Created Free stream velocity over a flat plate with freestream conditions
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Created Freestream density over flat plate using Stanton number
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Created Freestream density over the flat under the freestream flow conditions
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Created Freestream Stanton number for flat plate
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Created Freestream velocity over flat plate using Stanton number
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Created Insulated flat plate, the strong interaction
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Created Insulated flat plate, the weak interaction
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Created Local heat transfer over flat plate using Stanton number
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Created Total enthalpy over a flat plate with freestream conditions
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Created Wall enthalpy over flat plate using Stanton number
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Verified Ratio of Stagnation and Static Density
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Verified Ratio of Stagnation and Static Temperature
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4 More Basic Compressible Flow Calculators
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Basics (2)
Verified Thermal conductance for given thermal resistance
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Verified Total thermal resistance for conduction through two resistances in parallel
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3 More Basics Calculators
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Basics (2)
Verified Mach Angle
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Verified Mayer's formula
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5 More Basics Calculators
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Created Exact pressure coefficient for blast wave theory
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Created Pressure coefficient combined with blast wave for the shuttle
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Created Pressure coefficient combined with blast wave for the shuttle at angle of attack
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Created Pressure coefficient for blast wave theory at very high values of mach
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Created Pressure coefficient for Blunt-nosed cylinder:
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Created Pressure coefficient for Blunt-nosed plate:
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Verified Tension in the string
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1 More Bodies connected by a string - one hanging free, other lying on a rough horizontal plane Calculators
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Verified Acceleration of the system
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Verified Coefficient of friction for given tension
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Verified Inclination of plane for given frictional force
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Verified Mass of body B for given frictional force
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Verified Tension in the string
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2 More Bodies connected by a string - one hanging free, other lying on a rough inclined plane Calculators
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Verified Acceleration of the system
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Verified Angle of inclination for given acceleration
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Verified Angle of inclination for given tension
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1 More Bodies connected by a string - one hanging free, other lying on a smooth inclined plane Calculators
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Verified Frictional force on body A
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5 More Bodies connected by a string and lying on rough inclined planes Calculators
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Verified Acceleration of the system
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Verified Tension in the string
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2 More Bodies connected by a string and lying on smooth inclined planes Calculators
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Created Atomic Radius in BCC
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Created Lattice Constant of BCC
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Created Total volume of atoms in BCC
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Verified Area of surface for average drag coefficient in boundary layer flows
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Verified Coefficient of drag for Blasius's solution in boundary layer flow
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Verified Distance from leading edge for Blasius's solution in boundary layer flow
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Verified Distance from leading edge in boundary layer flow
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Verified Length of the plate for Reynold number in the laminar boundary layer flow
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Verified Reynold number at the end of the plate
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Verified Reynold number for drag coefficient in Blasius's solution of boundary layer flow
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Verified Shear stress at the boundary for turbulent boundary layer over a flat plate
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Verified Thickness of boundary layer for Blasius's solution in boundary layer flow
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Verified Thickness of boundary layer in boundary layer flow
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Verified Velocity of fluid for Reynold number in the laminar boundary layer flow
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10 More Boundary layer flow Calculators
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Created Adiabatic wall enthalpy using Stanton number
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Created Enthalpy of wall using Stanton number
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Created Local heat-transfer rate calculation using Stanton number
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Created local heat-transfer rate using Nusselt's number
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Created local shear stress at the wall
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Created Local skin-friction coefficient
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Created Nusselt number for hypersonic vehicle
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Created Nusselt's number with Reynolds number, the Stanton number and Prandtl number
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Created Prandtl number with Reynolds number, Nusselt's number, Stanton number and Stanton number
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Created Reynolds number for given Nusselt's number, Stanton number and Prandtl number
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Created Skin friction coefficient for incompressible flow
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Created Stanton number for hypersonic vehicle
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Created Stanton number with Reynolds number, Nusselt's number, Stanton number and Prandtl number
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Created Static Density equation using skin friction coefficient
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Created Static density equation using Stanton number
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Created Static velocity equation using skin friction coefficient
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Created Static velocity using Stanton number
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Created Static viscosity relation using temperature of wall
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Created Thermal conductivity at the edge of the boundary layer equation using Nusselt's number
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Created viscosity around the wall
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Verified Angle of heel for metacentric height in experimental method
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Verified Meta-centric height in the experimental method
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Verified Movable weight for metacentric height in experimental method
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6 More Buoyancy Calculators
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Verified Absolute temperature for the velocity of sound wave in the isothermal process
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Verified Absolute temperature for velocity of sound wave in terms of adiabatic process
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Verified Density of fluid considering velocity at outlet of orifice
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Verified Pressure ratio for maximum flow rate through nozzle or orifice
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Verified Stagnation temperature considering the compressible fluid flow
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Verified Temperature of fluid for stagnation temperature considering compressible fluid flow
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Verified Velocity of sound wave in terms of an adiabatic process
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Verified Velocity of sound wave in terms of isothermal process
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16 More Compressible flow Calculators
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Created Emissivity
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Created Freestream density
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Created Freestream velocity
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Created Reference viscosity
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Verified Sidewash angle
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Verified Vertical tail moment arm for given lift curve slope
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13 More Contribution of Aircraft Components (Part 1) Calculators
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Verified Dynamic pressure at vertical tail for given yawing moment coefficient
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Verified Sidewash angle for given yawing moment coefficient
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Verified Vertical tail area 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 Yawing moment coefficient for given vertical tail lift curve slope
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9 More Contribution of Aircraft Components (Part 2) Calculators
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Verified Dynamic pressure at vertical tail for given vertical tail efficiency
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Verified Dynamic pressure at wing for given vertical tail efficiency
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Verified Vertical tail efficiency
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Verified Vertical tail volume ratio for given yawing moment coefficient
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11 More Contribution of Aircraft Components (Part 3) Calculators
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Created Atomic Packing Factor
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Verified Total thermal resistance of 2 cylindrical resistances connected in series.
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Verified Total thermal resistance of 3 cylindrical resistances connected in series
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Verified Total thermal resistance of a cylindrical wall with convection either side
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11 More Cylinders Calculators
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Verified Coefficient of Drag for given thrust and weight
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Verified Lift-induced drag coefficient for given required thrust
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5 More Drag during Level Unaccelerated Flight Calculators
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Verified Actual discharge in venturimeter
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Verified Difference in pressure head for heavier liquid in manometer
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Verified Difference in pressure head for light liquid in manometer
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Verified Velocity at any point for coefficient of pitot-tube
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2 More Dynamics of fluid flow Calculators
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Created Emissivity per unit mole
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Created Kinetic energy per mole
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Created Kinetic energy per mole using molar volume
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Created Kinetic energy per mole using temperature of gas
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Created Mean free path of a single-species gas,
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Created Mean free path using number density
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Created Molar volume using kinetic energy per mole
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Created Number density
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Created Pressure of gas using number density
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Created Pressure using kinetic energy per mole
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Created Pressure using molar volume
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Created Specific gas constant using kinetic energy per mole
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Created Temperature of gas using Emissivity per unit mole
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Created Temperature of gas using kinetic energy per mole
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Created Volume of gas
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Verified Flight velocity for given elevator hinge moment coefficient
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4 More Elevator Hinge Moment Calculators
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Created Atomic Radius in FCC
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Created Lattice Constant of FCC
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Created Volume of atoms in FCC
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Created Adiabatic wall enthalpy for flat plate
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Created Adiabatic wall enthalpy using recovery factor
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Created Coefficient of friction using Stanton number for flat plat case
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Created Drag per unit span
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Created Overall skin-friction drag Coefficient
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Created Prandtl number for flat plate viscous flow
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Created Recovery factor calculation using Prandtl number
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Created Recovery factor for flat plate with viscous flow
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Created Recovery Factor using temperature
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Created Skin-friction drag for flat plate in viscous flow
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Created Stanton number using aerodynamic heating equation
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Created Stanton number with coefficient of friction
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Created Static density equation using aerodynamic equation
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Created Static velocity equation using aerodynamic heating equation
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Created Total enthalpy in the inviscid flow outside the boundary layer
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Verified Lift Coefficient for a given wing loading and turn radius
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Verified Wing loading for a given turn radius
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13 More Flight Envelope Calculators
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Verified Bazin's constant
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Verified Chezy's constant considering Bazin formula
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Verified Chezy's constant considering velocity
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Verified Critical depth considering flow in open channels
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Verified Critical depth considering minimum specific energy
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Verified Critical depth considering the critical velocity
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Verified Critical velocity considering flow in open channels
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Verified Discharge per unit width considering flow in open channels
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Verified Hydraulic mean depth considering Bazin formula
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Verified Hydraulic mean depth using Chezy's formula
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Verified Minimum specific energy considering the critical depth
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Verified Velocity of Chezy's formula
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7 More Flow in open channels Calculators
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Verified Coefficient of contraction for sudden contraction
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Verified Difference in liquid level in three compound pipes with same friction coefficient
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Verified Efficiency of power transmission in flow through pipes
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Verified Head available at the base of the nozzle
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Verified Head loss due to friction for the efficiency of power transmission
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Verified Loss of head at the exit of pipe
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Verified Loss of head due to obstruction in a pipe
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Verified Maximum area of obstruction in the pipe
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Verified Power lost due to sudden enlargement
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Verified Power transmission through pipes
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Verified Retarding force for gradual closure of valves
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Verified Time taken by pressure wave to travel
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Verified Total head at the inlet of pipe for head available at the base of the nozzle
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Verified Total head available at inlet of pipe for efficiency of power transmission
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Verified Velocity at the outlet for head loss at the exit of pipe
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Verified Velocity of fluid for head loss due to obstruction in a pipe
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Verified Velocity of liquid at vena-contracta
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22 More Flow through pipes Calculators
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Verified Circulation for a single stagnation point
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Verified Coefficient of drag for sphere in Oseen formula when Reynolds number is between 0.2 and 5
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Verified Coefficient of drag for sphere in stoke's law when Reynolds number is less than 0.2
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Verified Drag force for a body moving in a fluid of certain density
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Verified Freestream velocity for a single stagnation point
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Verified Radius of the cylinder for a single stagnation point
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Verified Tangential velocity for a single stagnation point
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Verified Total drag force on a sphere
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23 More Forces on sub-merged bodies Calculators
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Verified Airspeed measurement by Pitot tube for low-speed incompressible flow
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Verified Lift per unit span by Kutta-Joukowski theorem
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Verified Pressure at an upstream point on streamline by Bernoulli's equation
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Verified Pressure Coefficient
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Verified Pressure coefficient in terms of velocity ratio for inncompressible flow
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Verified Radial velocity for non-lifting flow over circular cylinder
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Verified Static pressure in incompressible flow
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Verified Stream function for flow over Rankine oval
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Verified Stream function for uniform incompressible flow in polar coordinates
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Verified Surface pressure coefficient for non-lifting flow over circular cylinder
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Verified Tangential velocity for 2-D Vortex flow
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Verified Tangential velocity for lifting flow over circular cylinder
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Verified Velocity potential for 2-D doublet flow
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Verified Velocity potential for 2-D source flow
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Verified Velocity potential for uniform incompressible flow in polar coordinates
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32 More Fundamentals of Inviscid Incompressible flow Calculators
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Verified Lift for given glide angle
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Verified Lift-to-drag ratio for given glide angle
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3 More Gliding Flight Calculators
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Created Blunt-nosed flat plate pressure ratio (first approximation)
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Created Boltzmann constant for cylindrical blast wave
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Created Coefficient of drag equation using energy released from blast wave
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Created Energy for the blast wave
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Created formula For creation pressure for the planar blast wave
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Created Modified Energy for the cylindrical blast wave
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Created Modified pressure equation for cylindrical blast wave
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Created Modified Radial coordinate equation for cylindrical blast wave
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Created Pressure for the cylindrical blast wave
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Created Pressure ratio for blunt cylinder blast wave
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Created Pressure ratio for blunt slab blast wave
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Created Radial coordinate for the planar blast wave,
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Created Radial coordinate of blunt slab blast wave
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Created Radial coordinate of cylindrical blast wave
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Created Simplified pressure ratio for blunt cylinder blast wave
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Created Time required for the blast wave
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Created Blunt-nosed radial coordinate flat plate (first approximation):
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Created Forces acting on body along the flight path
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Created Forces acting Perpendicular to the body on the flight path
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Created Pressure ratio of Blunt-nosed cylinder (first approximation):
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Created Radial coordinate of Blunt-nosed cylinder (first approximation):
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Created Radius for the cylinder-wedge body shape
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Created Radius for the sphere-cone body shape
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Created Radius of curvature for the cylinder-wedge
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Created Radius of curvature for the sphere-cone body shape
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Created Axial force coefficient
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Created Coefficient of drag
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Created Coefficient of pressure with similarity parameters
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Created Deflection angle
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Created Drag force
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Created Dynamic pressure
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Created Dynamic pressure based on coefficient of lift
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Created Fourier’s law of heat conduction
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Created Hypersonic similarity parameter
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Created lift coefficient
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Created Lift Force
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Created Mach number
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Created Mach ratio at high mach number
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Created Moment coefficient
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Created Newtonian sine-squared law for pressure coefficient
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Created Normal Force Coefficient
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Created Pressure ratio for high Mach number
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Created Pressure ratio having high mach number with similarity constant
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Created Shear-stress distribution.
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Created Supersonic expression for pressure coefficient on a surface with local deflection angle θ
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Created Coefficient of pressure with slenderness ratio
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Created Non dimensional radius for hypersonic vehicles
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Created Non-dimensional density
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Created Non-dimensional density for high mach number
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Created Non-dimensional parallel velocity component for high mach number
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Created Non-dimensional perpendicular velocity component for high mach number
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Created Non-dimensional pressure
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Created Non-dimensional pressure for high mach number
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Created Slenderness ratio with cone radius for hypersonic vehicle
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Created Transformed conical variable
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Created Transformed conical variable with cone angle in hypersonic flow
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Created Transformed conical variable with wave angle
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Created Density before shock formation for compression wave
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Created Density before the shock formation for expansion wave
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Created Detachment distance of cylinder-wedge
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Created Detachment distance of sphere cone
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Created Grid point calculation for shock waves
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Created Local shock velocity equation
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Created Mach wave behind the shock
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Created Mach wave behind the shock with mach infinity
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Created New pressure after the shock formation for compression wave
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Created New pressure after the shock formation, subtracted to velocity for expansion wave
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Created Nose radius of cylinder-wedge
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Created Nose radius of sphere cone
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Created Pressure ratio for unsteady waves
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Created Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves
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Created Ratio of new and old temperature
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Created Ratio of new and old temperature for expansion waves
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Created Temperature ratio for unsteady compression waves
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Created Temperature ratio for unsteady expansion wave
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Created Change in velocity for hypersonic flow in x direction
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Created Coefficient of pressure with slenderness ratio
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Created Coefficient of pressure with slenderness ratio and similarity constant
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Created Constant g used for finding the location of perturbed shock
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Created Density ratio with similarity constant having slenderness ratio
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Created Distance from tip of the leading edge to the base
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Created Doty and Rasmussen - normal-force coefficient
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Created Inverse of density for hypersonic flow
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Created Inverse of density for hypersonic flow using mach number
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Created Non dimensional Change in hypersonic disturbance velocity in x direction
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Created Non dimensional Change in hypersonic disturbance velocity in y direction
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Created Non dimensional pressure equation with slenderness ratio
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Created Non dimensional Velocity disturbance in y direction in hypersonic flow
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Created Non- dimensionalised time
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Created Rasmussen closed-form expression for the shock-wave angle
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Created Similarity constant equation using the wave angle
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Created Similarity constant equation with slenderness ratio
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Created Boundary-layer momentum thickness using Reynolds number at transition point
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Created Eddy viscosity calculation
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Created Local Mach Number using Reynolds number equation at transition region
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Created Location of the transition point
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Created Prandtl number of the transition flow
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Created Reynolds number equation using boundary-layer momentum thickness
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Created Reynolds number equation using local Mach number
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Created Specific heat at constant pressure for transient flow
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Created Static density at transition point
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Created Static density equation using boundary-layer momentum thickness
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Created Static velocity at transition point
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Created Static velocity using boundary-layer momentum thickness
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Created Static viscosity at transition point
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Created Static viscosity equation using boundary-layer momentum thickness
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Created Thermal conductivity of the transition flow
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Created Transition Reynolds number
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Created Large Mach number over a flat plate using static temperature and wall temperature
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Created Mach number over a flat plate using static temperature and wall temperature
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Created Pressure ratio for cold-wall case the strong interaction
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Created Pressure ratio for cold-wall case the weak interaction
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Created Static density of fluid over the flat plate
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Created Static temperature of fluid over the flat plate
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Created Static temperature of the plate using the wall viscosity
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Created Static temperature over a flat plate under viscous, very high Mach flow
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Created Static temperature over a flat plate using Static Mach Number
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Created Static viscosity using wall temperature and static temperature
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Created Total temperature over a flat plate under viscous Mach flow
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Created Total temperature over a flat plate under viscous very high Mach flow
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Created viscosity of wall using wall temperature and static temperature
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Created Wall density of fluid over the flat plate
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Created Wall temperature of fluid over the flat plate
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Created Wall temperature of the plate using the wall viscosity
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Created Wall temperature over a flat plate under viscous, very high Mach flow
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Created Wall temperature over a flat plate using Static Mach Number
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Verified Radius of the Rankine circle
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14 More Ideal flow or Potential flow Calculators
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Verified Boundary layer thickness for Turbulent flow
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Verified Center of pressure location for cambered airfoil
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Verified Skin friction drag coefficient for flat plate in laminar flow
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Verified Skin friction drag coefficient for flat plate in Turbulent flow
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4 More Incompressible flow over airfoil Calculators
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Verified Height or depth of paraboloid for volume of air
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Verified Total pressure force at the bottom of the cylinder
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Verified Total pressure force on top of the cylinder
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4 More Kinematics of flow Calculators
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Created Dynamic pressure
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Created Newtonian pressure distribution over the surface using cosine angle
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Created Nusselt number at the stagnation point
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Created Nusselt number for stagnation point on blunt body
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Created Reynolds analogy factor in Finite deference method
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Created Reynolds analogy for Stanton number in finite difference method
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Created Stagnation pressure
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Verified Landing ground roll distance
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Verified Landing ground roll distance using thrust reversal
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3 More Landing Performance Calculators
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Created Area of shear plane for given shear angle, width of cut & uncut chip thickness
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Created Coefficient of friction for given forces normal and along the tool rake face
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Created Coefficient of friction for given friction angle
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Created Coefficient of friction for given thrust force, cutting force and normal rake angle
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Created Cutting force for given force acting normal to the rake face, thrust force and normal rake angle
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Created Force acting normal to the rake face for given cutting force, thrust force and normal rake angle
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Created Side cutting edge angle for a given width of cut
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Created Thrust force for given force normal to the rake face, cutting force and normal rake angle
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Created Thrust force for given frictional force along tool rake face, cutting force & normal rake angle
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Created Width of cut for given side cutting edge angle
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28 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
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Created Convective heat transfer to the surface
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Created Radiative heat transfer to the surface stemming from thermal radiation
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Created Coefficient of drag equation with angle of attack
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Created Coefficient of drag equation with coefficient of normal force
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Created Coefficient of lift equation with angle of attack
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Created Coefficient of lift equation with coefficient of normal force
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Created Drag force with angle of attack
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Created exact normal shock-wave maximum coefficient of pressure
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Created Force F exerted on the surface
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Created Lift force with angle of attack
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Created Mass flux incident on a surface area
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Created Maximum Pressure coefficient
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Created Modified Newtonian Law
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Created Pressure coefficient for slender 2-D bodies
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Created Pressure coefficient for slender bodies of revolution
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Created Time rate of change of momentum of the mass flux
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Verified Characteristic Mach number
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Verified Critical speed of sound from Prandtl relation
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Verified Enthalpy ahead of normal shock from normal shock energy equation
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Verified Enthalpy behind of normal shock from normal shock energy equation
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Verified Mach Number behind the shock
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Verified Prandtl Condition
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Verified Velocity ahead of normal shock by normal shock momentum equation
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Verified Velocity behind of normal shock by normal shock momentum equation
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Verified Velocity upstream of shock using Prandtl relation
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20 More Normal Shock Waves Calculators
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Verified Coefficient of discharge for time required to empty a reservoir
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Verified Length of crest of the weir or notch
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Verified Time required to empty a reservoir
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24 More Notches and Weirs Calculators
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Verified Component of Upstream Mach normal to oblique shock
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18 More Oblique Shock and Expansion Waves Calculators
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Created Coefficient of pressure derived from oblique shock theory
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Created Density ratio when Mach become infinite
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Verified Dynamic pressure for given specific heat ratio and Mach number
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Created Exact Density Ratio
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Created Exact pressure ratio
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Created Exact relation for pressure coefficient behind an oblique shock wave
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Created Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite
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Created Non-dimensional pressure coefficient
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Created Parallel upstream flow components after shock as Mach tends to infinite
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Created Perpendicular upstream flow components behind the shock wave
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Created Pressure ratio when Mach becomes infinite
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Created Temperature ratio when Mach becomes infinite
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Created Temperature ratios
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Created Velocity of sound using dynamic pressure and density
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Created Wave angle for small deflection angle
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Verified Area at vena contracta for discharge and constant head
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Verified Area of mouthpiece In Borda's mouthpiece running free
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Verified Area of mouthpiece In Borda's mouthpiece running full
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Verified Area of orifice considering time of emptying a hemispherical tank
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Verified Co-efficient of contraction
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Verified Co-efficient of discharge considering time of emptying a hemispherical tank
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Verified Co-efficient of velocity
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Verified Discharge In Borda's mouthpiece running free
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Verified Discharge In Borda's mouthpiece running full
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Verified Discharge in the convergent-divergent mouthpiece
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Verified Head of the liquid above the centre of orifice
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Verified Horizontal distance for co-efficient of velocity and vertical distance
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Verified Time of emptying a hemispherical tank
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Verified Vertical distance for co-efficient of velocity and horizontal distance
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19 More Orifices and Mouthpieces Calculators
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Verified Interface temperature of composite wall of 2 layers when outer surface temperature is known
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Verified Total thermal resistance of a plain wall with convection on either side
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20 More Plane walls Calculators
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Verified Shaft brake power for reciprocating engine-propeller combination
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2 More Power Available and Maximum Velocity Calculators
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Verified Power required for given aerodynamic coefficients
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Verified Thrust required for given required power
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Verified Weight of aircraft for given required power
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7 More Power Required for Level Unaccelerated Flight Calculators
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Verified Endurance for given Lift-to-Drag ratio of Jet Airplane
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Verified Lift-to-Drag ratio for given Endurance of Jet Airplane
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Verified Range of Jet Airplane
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Verified Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
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Verified Thrust-Specific Fuel Consumption for given Range of Jet Airplane
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2 More Range and Endurance of Jet Airplane Calculators
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Verified Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
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9 More Range and Endurance of Propeller-Driven Airplane Calculators
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Verified Rate of Climb
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Verified Rate of Climb for given excess power
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Verified Weight of aircraft for given excess power
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7 More Rate of Climb Calculators
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Created Chord length for flat plate case
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Created Local Reynolds number
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Created local skin-friction coefficient
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Created Local turbulent skin-friction coefficient for incompressible flow
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Created Mach number at reference temperature
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Created Overall skin-friction drag coefficient
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Created Overall skin-friction drag coefficient for incompressible flow
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Created Reference temperature equation
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Created Reynolds number for chord length
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Created Reynolds number for chord length using the Overall skin-friction drag coefficient
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Created Stanton Number obtained from classical theory
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Created Static density of the plate using chord length for flat plate case
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Created Static velocity of the plate using chord length for flat plate case
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Created Static viscosity of the plate using chord length for flat plate case
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Created Turbulent flat-plate skin-friction coefficient
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Created Wall temperature using the reference temperature
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Verified Control stick length for given gearing ratio
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Verified Elevator chord length for given stick force
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Verified Elevator deflection angle for given gearing ratio
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Verified Elevator Stick force for given gearing ratio
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Verified Hinge moment coefficient for given stick force
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13 More Relationship between Stick Force and Hinge Moment Calculators
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Created Atomic Radius in SCC
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Created Lattice Constant of SCC
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Created Total volume of atoms in SCC
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Created Coefficient of pressure equation using specific heat ratio
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Created curvilinear grid location equation
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Created Density equation using enthalpy and pressure
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Created Enthalpy equation using coefficient of pressure for calorically perfect gas
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Created Enthalpy equation using pressure and density
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Created Enthalpy equation using specific heat ratio
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Created Free stream enthalpy
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Created local shock-layer thickness
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Created pressure equation using Enthalpy and density
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Created Total enthalpy
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Created total enthalpy equation using specific heat ratio and velocities
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Verified Heat flow rate through a spherical wall
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Verified Thermal resistance of a spherical wall
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9 More Spheres Calculators
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Verified Angle of incidence of wing
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Verified Mean aerodynamic chord for given tail pitching moment coefficient
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Verified Vertical tail moment arm for given yawing moment coefficient
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18 More Tail Contribution Calculators
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Verified Horizontal tail volume ratio for given pitching moment coefficient
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Verified Tail Efficiency for given tail volume ratio
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Verified Tail lift coefficient for given tail volume ratio
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Verified Tail Pitching moment coefficient for given tail volume ratio
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10 More Tail Contribution (Contd.) Calculators
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Verified Liftoff velocity for given stall velocity
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13 More Takeoff Performance Calculators
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Verified Minimum Thrust required for given weight
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Verified Thrust-to-weight ratio
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10 More Thrust Required for Level Unaccelerated Flight Calculators
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Verified Shear stress developed for turbulent flow in pipes
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Verified Shear velocity for turbulent flow in pipes
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5 More Turbulent flow Calculators
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Verified Weight during level turn
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11 More Turning Flight Calculators
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Verified Angular speed of outer cylinder in rotating cylinder method
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Verified Diameter of pipe for difference in pressure in viscous flow
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Verified Diameter of pipe for head loss due to friction in viscous flow
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Verified Diameter of pipe for loss of pressure head in viscous flow
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Verified Length of pipe for difference of pressure in viscous flow
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Verified Length of pipe for head loss due to friction in viscous flow
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Verified Length of pipe for loss of pressure head in viscous flow
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Verified Loss of head due to friction
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Verified Loss of pressure head for viscous flow through circular pipe
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Verified Maximum velocity at any radius with a velocity, and radius of pipe
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Verified Radius of pipe from maximum velocity and velocity at any radius
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Verified Total torque measured by strain in rotating cylinder method
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Verified Velocity at any radius, radius of pipe, and maximum velocity
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Verified Velocity of piston or body for movement of piston in dash-pot
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Verified Viscosity of fluid or oil for movement of piston in dash-pot
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Verified Viscosity of fluid or oil in rotating cylinder method
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36 More Viscous flow Calculators
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Created Aerodynamic heating to the surface
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Created Chapman–Rubesin factor
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Created Coefficient of friction using Stanton equation for incompressible flow
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Created Density calculation using Chapman–Rubesin factor
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Created internal energy for hypersonic flow
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Created Non dimensional internal energy parameter
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Created Non dimensional internal energy parameter using wall-to-freestream temperature ratio
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Created Non dimensional static enthalpy
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Created Stanton equation using Overall skin friction coefficient for incompressible flow
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Created Stanton number for incompressible flow
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Created Static Density calculation using Chapman–Rubesin factor
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Created Static enthalpy
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Created Static viscosity calculation using Chapman–Rubesin factor
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Created Thermal conductivity using Prandtl number
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Created Viscosity calculation using Chapman–Rubesin factor
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Created Wall temperature calculator due to internal energy
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