Calculators Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
https://www.linkedin.com/in/imvk93/
339
Formulas Created
143
Formulas Verified
72
Across Categories

List of Calculators by Vinay Mishra

Following is a combined list of all the calculators that have been created and verified by Vinay Mishra. Vinay Mishra has created 339 and verified 143 calculators across 72 different categories till date.
Created Aerodynamic axial force
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Created Aerodynamic normal force
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Created Aerodynamic side force
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Created Angle of attack
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Created Normal force coefficient with aerodynamic normal force
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Created Pitching moment
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Created Pitching moment coefficient
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Created Rolling moment
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Created Rolling moment coefficient
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Created Side force coefficient
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Created Sideslip angle
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Created Velocity along pitch axis for small sideslip angle
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Created Velocity along roll axis for small angle of attack
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Created Velocity along roll axis for small sideslip angle
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Created Velocity along yaw axis for small angle of attack
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Created Yawing moment
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Created Yawing moment coefficient
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Created Power required at an altitude
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Created Power required at an altitude for given power required at sea-level condition
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Created Power required at sea-level condition
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Created Velocity at an altitude
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Created Velocity at an altitude for given velocity at sea-level condition
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Created Velocity at sea-level condition
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Verified Adiabatic wall enthalpy over flat plate using Stanton number
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Verified Freestream density over flat plate using Stanton number
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Verified Freestream velocity over flat plate using Stanton number
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Verified Wall enthalpy over flat plate using Stanton number
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11 More Approximate Results Applied to Hypersonic Vehicles Calculators
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Verified Critical Density
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Verified Critical Pressure
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Verified Critical Temperature
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Created Ratio of Stagnation and Static Density
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Created Ratio of stagnation and static pressure
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Created Ratio of Stagnation and Static Temperature
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Basics (7)
Verified Isentropic compressibility for given density and speed of sound
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Created Mach Angle
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Created Mach Number
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Created Mayer's formula
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Created Speed of Sound
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Created Stagnation Temperature
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Verified Thermal resistance for conduction through 2 resistances in parallel
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Basics (2)
Verified Total thermal resistance for conduction through three resistances in series
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Verified Total thermal resistance for conduction through two resistances in series
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3 More Basics Calculators
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Verified Pressure coefficient for blast wave theory at very high values of mach
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Verified Pressure coefficient for Blunt-nosed plate:
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4 More Blast-wave part 2 Calculators
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Created Acceleration of the system with bodies one hanging free and other lying on a rough horizontal plane
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Created Tension in the string if coefficient of friction of horizontal plane is given
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Created Acceleration of the system with bodies one hanging free, other lying on a rough inclined plane
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Created Coefficient of friction for given frictional force
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Created Coefficient of friction for given tension
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Created Frictional force
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Created Inclination of plane for given frictional force
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Created Mass of body B for given frictional force
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Created Tension in the string if coefficient of friction of inclined plane is given
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Created Acceleration in the system
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Created Tension in the string if only one body is freely suspended
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Created Acceleration of the system with bodies one hanging free and other lying on a smooth inclined plane
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Created Angle of inclination for given acceleration
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Created Angle of inclination for given tension
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Created Tension in the string when one body is lying on smooth inclined plane
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Created Acceleration of the system for given mass of body A
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Created Acceleration of the system for given mass of body B
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Created Frictional force on body A
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Created Frictional force on body B
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Created Tension in the string for given mass of body A
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Created Tension in the string for given mass of body B
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Created Acceleration of the system with bodies connected by a string and lying on smooth inclined planes
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Created Angle of inclination of plane with body A
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Created Angle of inclination of plane with body B
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Created Tension in the string if both the bodies are lying on smooth inclined planes
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Created Acceleration of the bodies
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Created Mass of body B (smaller mass)
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Created Tension in the string if both the bodies are freely hanging
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Verified Average coefficient of drag for drag force in boundary layer flows
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Verified Drag force for average drag coefficient in boundary layer flows
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Verified Freestream velocity for local drag coefficient in boundary layer flows
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Verified Local drag coefficient for shear stress in boundary layer flows
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Verified Shear stress for local drag coefficient in boundary layer flows
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16 More Boundary layer flow Calculators
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Verified Local skin-friction coefficient
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Verified Stanton number with Reynolds number, Nusselt's number, Stanton number and Prandtl number
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18 More Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions Calculators
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Verified Centre of Buoyancy
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Verified Meta-centric height for time period of oscillation and radius of gyration
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Verified Radius of gyration for metacentric height and time period of oscillation
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Verified Volume of fluid displaced
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5 More Buoyancy Calculators
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Verified Bulk modulus for the velocity of sound wave
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Verified Velocity of sound wave in terms of bulk modulus
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22 More Compressible flow Calculators
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Created Moment produced by vertical tail for given lift curve slope
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Created Moment produced by vertical tail for given side force
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Created Sideslip angle for an Aircraft
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Created Sideslip angle for given moment produced by vertical tail
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Created Sidewash angle
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Created Vertical tail angle of attack
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Created Vertical tail angle of attack for given vertical tail side force
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Created Vertical tail area for given vertical tail side force
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Created Vertical tail dynamic pressure for given vertical tail side force
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Created Vertical tail lift curve slope
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Created Vertical tail lift curve slope for given moment
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Created Vertical tail moment arm for given lift curve slope
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Created Vertical tail moment arm for given side force
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Created Vertical tail Side force
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Created Vertical tail side force for given moment
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Created Dynamic pressure at vertical tail for given yawing moment coefficient
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Created Moment produced by vertical tail for given moment coefficient
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Created Sideslip angle for given yawing moment coefficient
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Created Sidewash angle for given moment produced by vertical tail
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Created Sidewash angle for given yawing moment coefficient if wingspan is given
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Created Vertical tail area for given moment
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Created Vertical tail area for given yawing moment coefficient
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Created Vertical tail dynamic pressure for given moment
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Created Vertical tail lift curve slope for given yawing moment coefficient
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Created Wing area for given moment produced by vertical tail
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Created Wing dynamic pressure for given yawing moment coefficient
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Created Wingspan for given yawing moment coefficient
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Created Yawing moment coefficient for given vertical tail lift curve slope
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Created Yawing moment coefficient when wingspan is given
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Created Dynamic pressure at vertical tail for given vertical tail efficiency
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Created Dynamic pressure at wing for given vertical tail efficiency
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Created Dynamic pressure at wing for given yawing moment coefficient
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Created Vertical tail area for given vertical tail volume ratio
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Created Vertical tail efficiency
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Created Vertical tail efficiency for given yawing moment coefficient
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Created Vertical tail lift curve slope for given yawing moment coefficient and Vertical Tail Efficiency
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Created Vertical tail moment arm for given vertical tail volume ratio
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Created Vertical tail volume ratio
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Created Vertical tail volume ratio for given yawing moment coefficient
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Created Wing area for given vertical tail volume ratio
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Created Wing area for given yawing moment coefficient
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Created Wingspan for given vertical tail volume ratio
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Created Wingspan for given yawing moment coefficient when sideslip angle and sidewash angle are given
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Created Yawing moment coefficient for given vertical tail volume ratio
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Created Sideslip angle for given yawing moment coefficient if vertical tail volume ratio is given
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Created Sidewash angle for given yawing moment coefficient
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Verified Heat flow rate through a cylindrical composite wall of 2 layers
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Verified Heat flow rate through a cylindrical composite wall of 3 layers
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Verified Heat flow rate through a cylindrical wall
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Verified Inner surface temperature of a cylindrical wall for a given heat flow rate
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Verified Outer surface temperature of a cylindrical wall for a given heat flow rate
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Verified Outer surface temperature of the cylindrical composite wall of 2 layers
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Verified Thermal conductivity of a cylindrical wall for a given temperature difference
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Verified Thermal resistance for radial heat conduction offered by a cylinder wall
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6 More Cylinders Calculators
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Created Coefficient of Drag for given thrust and weight
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Created Coefficient of Drag for given thrust-to-weight ratio
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Created Drag for a level, unaccelerated flight at negligible thrust angle
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Created Lift-induced drag coefficient for given required thrust
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Created Zero-lift drag coefficient at minimum required thrust
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Created Zero-lift drag coefficient for given lift coefficient
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Created Zero-lift drag coefficient for given required thrust
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Created Elevator area for given hinge moment coefficient
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Created Elevator chord length for given hinge moment coefficient
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Created Elevator Hinge moment coefficient
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Created Elevator Hinge moment for given hinge moment coefficient
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Created Flight velocity for given elevator hinge moment coefficient
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Created Centrifugal Force in an accelerated flight
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Created Drag for a level, unaccelerated flight
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Created Drag in an accelerated flight
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Created Lift for an unaccelerated flight
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Created Lift in an accelerated flight
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Created Thrust angle for an unaccelerated flight for given drag
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Created Thrust angle for an unaccelerated flight for given lift
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Created Thrust for a level, unaccelerated flight
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Created Thrust in an accelerated flight
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Created Velocity in an accelerated flight
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Created Weight of aircraft in level, unaccelerated flight
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Verified Recovery factor calculation using Prandtl number
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Verified Recovery factor for flat plate with viscous flow
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Verified Skin-friction drag Coefficient
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12 More Flat-Plate for Viscous flow case Calculators
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Created Lift Coefficient for a given turn radius
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Created Lift Coefficient for a given turn rate
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Created Lift Coefficient for a given wing loading and turn radius
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Created Load factor for a given turn radius for a high-performance fighter aircraft
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Created Load factor for a given turn rate for a high-performance fighter aircraft
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Created Radius of turn for a given lift coefficient
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Created Radius of turn for a given wing loading
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Created Turn radius for a high load factor
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Created Turn rate for a given lift coefficient
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Created Turn rate for a given wing loading
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Created Turn rate for a high load factor
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Created Velocity for a given turn radius for a high load factor
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Created Velocity for a given turn rate for a high load factor
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Created Wing loading for a given turn radius
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Created Wing loading for a given turn rate
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Verified Intensity of pressure wave produced for gradual closure of valves
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Verified Loss of head due to bead in a pipe
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Verified Loss of head due to sudden enlargement at any particular section of pipe
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Verified Time required to close the valve for gradual closure of valves
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Verified Velocity at section 1-1 for sudden enlargement
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Verified Velocity at section 2-2 for sudden enlargement
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33 More Flow through pipes Calculators
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Created Friction Coefficient
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Verified Circulation for lift force on a cylinder
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Verified Freestream velocity for lift coefficient in a rotating cylinder with circulation
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Verified Freestream velocity for lift coefficient with tangential speed
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Verified Length of the cylinder for lift force on a cylinder
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Verified Lift coefficient for a rotating cylinder with circulation
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Verified Lift coefficient for a rotating cylinder with tangential speed
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Verified Lift force on a cylinder for circulation
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Verified Radius of cylinder for lift coefficient in a rotating cylinder with circulation
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Verified Tangential velocity of the cylinder with the lift coefficient
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22 More Forces on sub-merged bodies Calculators
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Verified Circulation by Kutta-Joukowski theorem
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Verified Height difference of manometric fluid for given pressure difference
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Verified Location of stagnation point outside the cylinder for lifting flow
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Verified Pressure at a downstream point on streamline by Bernoulli's equation
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Verified Pressure difference in the low-speed wind tunnel for given test section velocity
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Verified Radial velocity for lifting flow over circular cylinder
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Verified Radius of cylinder for non-lifting flow
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Verified Source Strength for 2-D incompressible source flow
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Verified Stagnation streamline equation for flow over semi-infinite body
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Verified Stream function for 2-D incompressible source flow
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Verified Stream function for non-lifting flow over a circular cylinder
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Verified Surface pressure coefficient for lifting flow over circular cylinder
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Verified Surface pressure on the body in terms of Pressure coefficient
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Verified Velocity at a point on airfoil for given pressure coefficient and free-stream velocity
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Verified Velocity potential for 2-D Vortex flow
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Verified Velocity potential for uniform incompressible flow
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31 More Fundamentals of Inviscid Incompressible flow Calculators
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Created Degree of freedom
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Created Number of Components
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Created Number of Phases
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Created Total Number of Variables in a System
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Created Drag for given glide angle
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Created Glide angle
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Created Glide angle for given lift-to-drag ratio
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Created Lift for given glide angle
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Created Lift-to-drag ratio for given glide angle
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Verified Coefficient of drag equation using energy released from blast wave
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Verified Modified Energy for the cylindrical blast wave
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14 More Hypersonic Equivalence Principle and Blast-Wave Theory Calculators
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Verified Axial force coefficient
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Verified Normal Force Coefficient
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18 More Hypersonic Flow Calculators
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Verified Transformed conical variable with cone angle in hypersonic flow
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10 More Hypersonic Inviscid Flowfields: Approximate Methods Calculators
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Verified Similarity constant equation using the wave angle
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16 More Hypersonic Small-Disturbance Equations Calculators
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Verified Reynolds number equation using boundary-layer momentum thickness
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Verified Reynolds number equation using local Mach number
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Verified Thermal conductivity of the transition flow
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13 More Hypersonic Transition Calculators
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Verified Wall temperature over a flat plate under viscous, very high Mach flow
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17 More Hypersonic Viscous Interactions Calculators
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Verified Radial velocity at any radius
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Verified Radius at any point considering radial velocity
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Verified Stream function at a point
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Verified Stream function at a point in the combined flow
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Verified Stream function in sink flow for angle
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Verified Strength of doublet for stream function
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Verified Strength of source for radial velocity and at any radius
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Verified Uniform flow velocity for stream function at a point in the combined flow
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7 More Ideal flow or Potential flow Calculators
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Verified Lift coefficient for symmetrical airfoil by Thin airfoil theory
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7 More Incompressible flow over airfoil Calculators
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Verified Reynolds analogy factor in Finite deference method
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Verified Reynolds analogy for Stanton number in finite difference method
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5 More Laminar boundary layer at a stagnation point on a blunt body, Calculators
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Created Landing ground roll distance
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Created Landing ground roll distance using thrust reversal
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Created Stall velocity for given touchdown velocity
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Created Touchdown velocity
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Created Touchdown velocity for given stall velocity
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Created Lift-to-drag ratio for given required thrust
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Created Thrust required for given Lift-to-drag ratio
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Created Weight of aircraft for given Lift-to-drag ratio
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Created Load factor for a given pull-down maneuver radius
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Created Load factor for a given pull-down maneuver rate
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Created Load factor for a given pull-up maneuver radius
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Created Load factor for a given pull-up maneuver rate
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Created Pull-down maneuver radius
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Created Pull-down maneuver rate
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Created Pull-up maneuver radius
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Created Pull-up maneuver rate
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Created Velocity for a given pull-down maneuver radius
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Created Velocity for a given pull-down maneuver rate
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Created Velocity for a given pull-up maneuver radius
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Created Velocity for a given pull-up maneuver rate
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Created Shear angle for given area of shear plane, width of cut & uncut chip thickness
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Created Shear force acting on shear plane for given shear stress & area of shear plane
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Created Shear force on shear plane for given shear stress, width of cut, uncut chip thickness & shear angle
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Created Uncut chip thickness for given width of cut, shear angle & area of shear plane
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Created Width of cut for given shear angle, uncut chip thickness & area of shear plane
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17 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
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Created Back Rake Angle
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Created Inclination Angle
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Created Orthogonal Rake Angle
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Created Side Rake Angle
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2 More Metal Cutting and tools Calculators
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Verified Radiative heat transfer to the surface stemming from thermal radiation
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1 More Modern design-oriented code Calculators
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Created Characteristic Mach number
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Created Characteristic Mach Number behind shock
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Verified Density ahead of normal shock using normal shock momentum equation
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Verified Density behind normal shock using normal shock momentum equation
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Verified Density ratio across a normal shock
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Created Entropy change across normal shock
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Created Mach Number behind the shock
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Created Prandtl Condition
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Verified Pressure ratio across a normal shock
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Created Relation between Characteristic Mach number and Mach number
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Created Shock strength
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Verified Stagnation pressure behind normal shock by Rayleigh Pitot tube formula
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Verified Static Pressure ahead of normal shock using normal shock momentum equation
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Verified Static Pressure behind of normal shock using normal shock momentum equation
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Verified Velocity ahead of normal shock from normal shock energy equation
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Created Velocity behind a normal shock
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Verified Velocity behind of normal shock from normal shock energy equation
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12 More Normal Shock Waves Calculators
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Verified Discharge over a broad-crested weir
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Verified Discharge over rectangle notch or weir
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Verified Discharge over rectangle weir for Bazin's formula with velocity approach
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Verified Discharge over rectangle weir with two end contractions
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Verified Head of liquid over the crest
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Verified Length of section for discharge over rectangle notch or weir
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Verified Length of weir considering Bazin's formula with velocity approach
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Verified Length of weir for Discharge over a broad-crested weir
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19 More Notches and Weirs Calculators
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Created Component of Downstream Mach normal to oblique shock
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Created Component of Upstream Mach normal to oblique shock
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Created Flow deflection angle
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Verified Prandtl Meyer function
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Verified Prandtl Meyer function at upstream Mach no.
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Verified Pressure behind expansion fan
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Verified Rearward Mach angle of the expansion fan
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Verified Temperature behind expansion fan
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11 More Oblique Shock and Expansion Waves Calculators
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Created Dynamic pressure for given specific heat ratio and Mach number
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Verified Velocity of sound using dynamic pressure and density
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13 More oblique shock relation Calculators
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Verified Co-efficient of discharge considering time of emptying a circular horizontal tank
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Verified Co-efficient of velocity for the head of liquid and head loss
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Verified Discharge through fully sub-merged orifice
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Verified Discharge through large rectangular orifice
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Verified Discharge through partially sub-merged orifice
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Verified Head of liquid for head loss and coefficient of velocity
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Verified Loss of head due to fluid resistance
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Verified Theoretical velocity
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Verified Time of emptying a circular horizontal tank
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24 More Orifices and Mouthpieces Calculators
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Verified Area of the plane wall required for a given temperature difference
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Verified Heat flow rate through a composite wall of 2 layers in series
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Verified Heat flow rate through a composite wall of 3 layers in series
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Verified Interface temperature of composite wall of 2 layers when inner surface temperature is known
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Verified Length of the 2nd layer of the composite wall for a given temperature difference
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Verified Outer surface temperature of a composite wall of 2 layers for a given heat flow rate
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Verified Outer surface temperature of a composite wall of 3 layers for a given heat flow rate
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Verified Outer surface temperature of the wall for a given heat flow rate
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Verified Thermal conductivity of the material required to maintain a given temperature difference
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Verified Thickness of the plane wall required for a given temperature difference
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12 More Plane walls Calculators
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Created Power available for reciprocating engine-propeller combination
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Created Propeller efficiency for reciprocating engine-propeller combination
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Created Shaft brake power for reciprocating engine-propeller combination
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Created Coefficient of Drag due to lift for minimum power required
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Created Freestream velocity for given required power
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Created Freestream Velocity for given total drag
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Created Power required for given aerodynamic coefficients
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Created Power required for given required thrust
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Created Power required for given total drag
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Created Thrust required for given required power
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Created Total drag for given required power
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Created Weight of aircraft for given required power
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Created Zero-lift drag coefficient for minimum power required
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Created Endurance for given Lift-to-Drag ratio of Jet Airplane
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Created Endurance of Jet Airplane
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Created Lift-to-Drag ratio for given Endurance of Jet Airplane
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Created Range of Jet Airplane
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Created Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
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Created Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane
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Created Thrust-Specific Fuel Consumption for given Range of Jet Airplane
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Created Endurance of Propeller-Driven Airplane
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Created Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
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Created Propeller Efficiency for given Endurance of Propeller-Driven Airplane
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Created Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane
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Created Propeller Efficiency for given Range of Propeller-Driven Airplane
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Created Range of Propeller-Driven Airplane
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Created Range of Propeller-Driven Airplane for given lift-to-drag ratio
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Created Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
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Created Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane
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Created Specific Fuel Consumption for given Range of Propeller-Driven Airplane
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Created Excess power
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Created Excess power for given rate of climb
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Created Flight path angle at a given rate of climb
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Created Rate of Climb
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Created Rate of Climb for given excess power
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Created Thrust available for given excess power
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Created Total Drag for given excess power
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Created Velocity of aircraft at a given rate of climb
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Created Velocity of aircraft for given excess power
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Created Weight of aircraft for given excess power
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Verified Local turbulent skin-friction coefficient for incompressible flow
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Verified Reynolds number for chord length using the Overall skin-friction drag coefficient
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Verified Turbulent flat-plate skin-friction coefficient
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12 More Reference Temperature Method Calculators
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Created Control stick length for given gearing ratio
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Created Elevator area for given stick force
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Created Elevator chord length for given stick force
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Created Elevator deflection angle for given gearing ratio
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Created Elevator deflection angle for given stick force
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Created Elevator Stick Force
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Created Elevator Stick force for given gearing ratio
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Created Elevator stick force for given hinge moment coefficient
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Created Flight velocity for given stick force
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Created Gearing ratio
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Created Gearing ratio for given hinge moment coefficient
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Created Gearing ratio for given stick force
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Created Hinge moment coefficient for given stick force
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Created Hinge moment for given gearing ratio
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Created Hinge moment for given stick force
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Created Stick deflection angle for given gearing ratio
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Created Stick deflection angle for given stick force
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Created Stick length for given stick force
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Created Dihedral angle for given sideslip velocity
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Created Forward velocity for given normal component of side velocity
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Created Normal component of side velocity for given dihedral angle
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Created Normal component of side velocity for given forward velocity
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Created Sideslip velocity for given dihedral angle
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Created Angle of attack at the tail
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Created Angle of attack of the wing
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Created Angle of incidence of tail
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Created Angle of incidence of wing
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Created Downwash angle
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Created Lift due to tail only
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Created Lift due to wing only
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Created Mean aerodynamic chord for given tail pitching moment coefficient
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Created Pitching moment due to tail
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Created Tail area for given tail efficiency
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Created Tail Efficiency for given lift coefficients
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Created Tail lift coefficient for given pitching moment
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Created Tail Lift Coefficient of wing-tail combination
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Created Tail lift for given tail pitching moment
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Created Tail Pitching moment coefficient
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Created Tail Pitching moment for given lift coefficient
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Created Tail Pitching moment for given moment coefficient
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Created Total Lift Coefficient of wing-tail combination
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Created Total Lift of wing-tail combination
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Created Vertical tail moment arm for given yawing moment coefficient
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Created Wing Lift Coefficient of wing-tail combination
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Created Horizontal tail area for given tail volume ratio
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Created Horizontal tail volume ratio
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Created Horizontal tail volume ratio for given pitching moment coefficient
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Created Tail area for given tail moment coefficient
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Created Tail Efficiency for given pitching moment coefficient
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Created Tail Efficiency for given tail volume ratio
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Created Tail lift coefficient for given pitching moment coefficient
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Created Tail lift coefficient for given tail volume ratio
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Created Tail moment arm for given horizontal tail volume ratio
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Created Tail moment arm for given tail moment coefficient
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Created Tail Pitching moment coefficient for given tail efficiency
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Created Tail Pitching moment coefficient for given tail volume ratio
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Created Wing Mean aerodynamic chord for given horizontal tail volume ratio
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Created Wing Reference area for given horizontal tail volume ratio
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Created Coefficient of rolling friction during ground roll
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Created Drag during ground effect
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Created Ground effect factor
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Created Lift acting on aircraft during ground roll
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Created Liftoff distance
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Created Liftoff velocity for given stall velocity
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Created Liftoff velocity for given weight
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Created Maximum Lift coefficient for given liftoff velocity
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Created Maximum Lift coefficient for given stall velocity
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Created Resistance force during ground roll
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Created Stall velocity for given liftoff velocity
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Created Stall velocity for given weight
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Created Thrust for given liftoff distance
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Created Weight of aircraft during ground roll
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Created Absolute altitude
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Created Geometric altitude
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Created Geometric altitude for given geopotential altitude
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Created Geopotential altitude
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Created Lapse rate
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Created Coefficient of Drag due to lift
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Created Drag Coefficient for given parasite drag coefficient
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Created Drag Coefficient for given zero-lift drag coefficient
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Created Parasite Drag Coefficient at zero lift
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Created Coefficient of Lift for given thrust and weight
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Created Coefficient of Lift for given thrust-to-weight ratio
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Created Lift coefficient for given minimum required thrust
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Created Lift for a level, unaccelerated flight at negligible thrust angle
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Created Minimum Thrust required
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Created Minimum Thrust required for given lift coefficient
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Created Minimum Thrust required for given weight
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Created Thrust for given coefficients of lift and drag
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Created Thrust required for level, unaccelerated flight
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Created Thrust-to-weight ratio
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Created Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
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Created Weight of aircraft for given coefficients of lift and drag
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Verified Discharge through pipe for power required and head loss in turbulent flow
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Verified Head loss due to friction for power required and discharge in turbulent flow
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5 More Turbulent flow Calculators
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Created Bank angle during level turn
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Created Lift during level turn
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Created Lift for a given load factor
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Created Load factor for a given turn radius
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Created Load factor for a given turn rate
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Created Load factor when Lift Force and Weight is Given
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Created Turn radius
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Created Turn rate
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Created Velocity for a given turn radius
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Created Velocity for a given turn rate
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Created Weight during level turn
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Created Weight for a given load factor
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Verified Buoyant force in falling sphere resistance method
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Verified Density of fluid in falling sphere resistance method
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Verified Diameter of sphere in falling sphere resistance method
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Verified Drag force in falling sphere resistance method
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Verified Velocity of sphere in falling sphere resistance method
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Verified Viscosity of fluid or oil in falling sphere resistance method
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46 More Viscous flow Calculators
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