Calculators Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
https://www.linkedin.com/in/imvk93/
338
Formulas Created
141
Formulas Verified
89
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 338 and verified 141 calculators across 89 different categories till date.
Verified Heat Flow Rate through Composite Wall of 2 Layers in Series
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Verified Interface Temperature of Composite Wall of 2 Layers given Inner Surface Temperature
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Verified Length of 2nd Layer of Composite Wall in Conduction through Walls
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Verified Outer Surface Temperature of Composite Wall of 2 Layers for Conduction
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4 More 2 Layers Calculators
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Verified Heat Flow Rate through Composite Wall of 3 Layers in Series
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Verified Outer Surface Temperature of Composite Wall of 3 Layers for Conduction
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4 More 3 Layers Calculators
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Verified Height Difference of Manometric Fluid for given Pressure Difference
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Verified Surface Pressure on Body using Pressure Coefficient
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Verified Wind Tunnel Pressure Difference with Test Speed
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7 More Aerodynamic Measurements and Wind Tunnel Testing Calculators
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Created Sideslip Angle for Aircraft
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Created Sideslip Angle for given Moment Produced by Vertical Tail
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Created SideSlip Angle for given Yawing Moment Coefficient
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Created Sideslip Angle given Yawing Moment Coefficient and Tail Efficiency
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Created Sidewash angle
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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
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Created Sidewash Angle given Yawing Moment Coefficient using Wingspan
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Created Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope
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Created Yawing Moment Coefficient for given Vertical Tail Volume Ratio
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Created Yawing Moment Coefficient using Wingspan
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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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1 More Aircraft Dynamics Nomenclature Calculators
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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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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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9 More Atmosphere and Gas Properties Calculators
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Verified Pressure at Downstream Point by Bernoulli's Equation
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Verified Velocity at Point on Airfoil for given Pressure Coefficient and Free-Stream Velocity
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4 More Bernoulli's Equation and Pressure Concepts 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 Theory Calculators
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Created Acceleration of System with Bodies One Hanging Free and Other Lying on Rough Horizontal Plane
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Created Tension in String given Coefficient of Friction of Horizontal Plane
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Created Acceleration of System given Mass of Body A
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Created Acceleration of System 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 String given Mass of Body A
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Created Tension in String given Mass of Body B
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Created Acceleration of System with Bodies One Hanging Free, Other Lying on Rough Inclined Plane
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Created Coefficient of Friction given Frictional Force
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Created Coefficient of Friction 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 given Frictional Force
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Created Tension in String given Coefficient of Friction of Inclined Plane
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Created Acceleration in System
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Created Tension in String if only One Body is Freely Suspended
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Created Acceleration of System with Bodies Connected by 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 String if Both Bodies are Lying on Smooth Inclined Planes
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Created Acceleration of System with Bodies One Hanging Free and Other Lying on Smooth Inclined Plane
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Created Angle of Inclination given Acceleration
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Created Angle of Inclination given Tension
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Created Tension in String when One Body is Lying on Smooth Inclined Plane
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Created Acceleration of Bodies
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Created Mass of Body B of Smaller Mass
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Created Tension in String if Both Bodies are Freely Hanging
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Verified Average Coefficient of Drag for Drag Force
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Verified Drag Force for Average Drag Coefficient
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Verified Freestream Velocity for Local Drag Coefficient
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Verified Local Drag Coefficient for Shear Stress
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Verified Shear Stress for Local Drag Coefficient
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16 More Boundary Layer Flow 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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7 More Buoyancy Calculators
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Created Centrifugal Force in Accelerated Flight
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Created Drag in Accelerated Flight
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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 given rate of climb
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Created Lift in Accelerated Flight
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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 Thrust in Accelerated Flight
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Created Total Drag for given Excess Power
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Created Velocity in Accelerated Flight
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Created Velocity of aircraft at 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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1 More Climbing Flight Calculators
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Verified Bulk Modulus for Velocity of Sound Wave
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Verified Velocity of Sound Wave given Bulk Modulus
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8 More Compressible Flow Parameters Calculators
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Verified Heat Flow Rate through Cylindrical Composite Wall of 2 Layers
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Verified Heat Flow Rate through Cylindrical Composite Wall of 3 Layers
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Verified Heat Flow Rate through Cylindrical Wall
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Verified Inner Surface Temperature of Cylindrical Wall in Conduction
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Verified Outer Surface Temperature of Cylindrical Composite Wall of 2 Layers
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Verified Outer Surface Temperature of Cylindrical Wall given Heat Flow Rate
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Verified Thermal Conductivity of Cylindrical Wall given Temperature Difference
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Verified Thermal Resistance for Radial Heat Conduction in Cylinders
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8 More Conduction in Cylinder Calculators
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Verified Circulation for Lift Force on Cylinder
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Verified Length of Cylinder for Lift Force on Cylinder
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5 More Cylinder Properties Calculators
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Verified Modified Energy for Cylindrical Blast Wave
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7 More Cylindrical Blast Wave Calculators
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Verified Stanton Number with Reynolds Number, Nusselt's Number, Stanton Number and Prandtl Number
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3 More Dimensionless Quantities Calculators
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Verified Diameter of Sphere in Falling Sphere Resistance Method
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18 More Dimensions and Geometry Calculators
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Verified Discharge over 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 of Approach
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Verified Discharge over Rectangle Weir with Two End Contractions
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Verified Head of Liquid at Crest
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12 More Discharge Calculators
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Created Characteristic Mach Number behind Shock
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Verified Density behind Normal Shock using Normal Shock Momentum Equation
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Created Mach Number behind Shock
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Verified Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula
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Verified Static Pressure behind Normal Shock using Normal Shock Momentum Equation
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Created Velocity behind Normal Shock
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Verified Velocity behind Normal Shock from Normal Shock Energy Equation
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8 More Downstream Shock Waves Calculators
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Verified Prandtl Meyer Function
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Verified Prandtl Meyer Function at Upstream Mach Number
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Verified Pressure behind Expansion Fan
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Verified Rearward Mach Angle of Expansion Fan
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Verified Temperature behind Expansion Fan
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5 More Expansion Waves Calculators
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Verified Viscosity of Fluid or Oil in Falling Sphere Resistance Method
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12 More Flow Analysis Calculators
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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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4 More Flow Head Calculators
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Verified Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory
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7 More Flow over Airfoils Calculators
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Verified Coefficient of Discharge given Time of Emptying Circular Horizontal Tank
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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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7 More Flow Rate Calculators
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Verified Time required to close 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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14 More Flow Regime Calculators
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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 Drag Force in Falling Sphere Resistance Method
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Verified Velocity of Sphere in Falling Sphere Resistance Method
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17 More Fluid Flow and Resistance Calculators
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Verified Freestream Velocity for Lift Coefficient in Rotating Cylinder with Circulation
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Verified Freestream velocity for lift coefficient with tangential speed
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7 More Fluid Parameters and Characteristics Calculators
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Created Cutting Shear Force given Uncut Chip Thickness and Shear Angle
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3 More Force Normal to Shear Calculators
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Created Shear force acting on shear plane for given shear stress and area of shear plane
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5 More Forces and Friction Calculators
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Verified Thermal resistance for conduction through 2 resistances in parallel
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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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7 More Fundamental of Heat Transfer Calculators
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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 of Approach
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Verified Length of Weir for Discharge over Broad-Crested Weir
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7 More Geometric DImension Calculators
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Created Shear angle for given area of shear plane, width of cut and uncut chip thickness
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Created Uncut chip thickness for given width of cut, shear angle and area of shear plane
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Created Width of cut for given shear angle, uncut chip thickness and area of shear plane
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5 More Geometry and Dimensions 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 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 Force for given Glide Angle
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Created Lift-to-drag ratio for given glide angle
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1 More Gliding Flight 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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Verified Isentropic Compressibility for given Density and Speed of Sound
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Created Mayer's Formula
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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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10 More Governing Equations and Sound Wave Calculators
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Created Lift Coefficient for given Turn Radius
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Created Lift Coefficient for given Turn Rate
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Created Lift Coefficient for given wing loading and turn radius
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Created Load factor for given turn radius for high-performance fighter aircraft
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Created Load factor for given turn rate for high-performance fighter aircraft
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Created Radius of Turn for given Lift Coefficient
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Created Radius of Turn for given Wing Loading
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Created Turn radius for high load factor
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Created Turn Rate for given Lift Coefficient
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Created Turn Rate for given Wing Loading
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Created Turn Rate for High Load Factor
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Created Velocity for given pull-up maneuver rate
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Created Velocity given Turn Radius for High Load Factor
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Created Wing Loading for given Turn Radius
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Created Wing Loading for given Turn Rate
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2 More High Load Factor Maneuver 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 Parameters Calculators
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Verified Local Skin-Friction Coefficient
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6 More Hypersonic Flow Parameters 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 Transition Flow
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13 More Hypersonic Transition 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 point
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Verified Stream Function at Point in 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 point in combined flow
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15 More Incompressible Flow Characteristics Calculators
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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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10 More Jet Airplane Calculators
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Verified Circulation by Kutta-Joukowski Theorem
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3 More Kutta Joukowski Lift Theorem 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 Stagnation point on Blunt body Calculators
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Created Landing ground roll distance
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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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1 More Landing Calculators
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Created Aircraft forward velocity for given normal component of side velocity
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Created Aircraft sideslip velocity for given dihedral angle
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Created Dihedral angle for given sideslip velocity
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Created Normal component of aircraft side velocity for given dihedral angle
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Created Normal component of aircraft side velocity for given forward velocity
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Verified Lift Coefficient for Rotating Cylinder with Circulation
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Verified Lift Coefficient for Rotating Cylinder with Tangential Speed
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Verified Lift Force on Cylinder for Circulation
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Verified Radius of Cylinder for Lift Coefficient in Rotating Cylinder with Circulation
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Verified Tangential Velocity of Cylinder with Lift Coefficient
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11 More Lift and Circulation Calculators
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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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17 More Lift and Drag Polar Calculators
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Created Coefficient of Drag due to Lift for Minimum Power required
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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 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 Drag for Level and Unaccelerated Flight
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Created Drag for Level and Unaccelerated Flight at Negligible Thrust Angle
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Created Freestream Velocity given required Power
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Created Freestream Velocity given Total Drag Force
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Created Lift Coefficient given Minimum required Thrust
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Created Lift for Level and Unaccelerated Flight at Negligible Thrust Angle
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Created Lift for Unaccelerated Flight
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Created Lift-Induced Drag Coefficient given required Thrust
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Created Lift-to-Drag Ratio given required Thrust of Aircraft
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Created Total Drag Force given required Power
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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 Minimum Power required
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Created Zero-Lift Drag Coefficient given required Thrust
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Verified Location of Stagnation Point Outside Cylinder for Lifting Flow
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Verified Radial Velocity for Lifting Flow over Circular Cylinder
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Verified Surface Pressure Coefficient for Lifting Flow over Circular Cylinder
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7 More Lifting Flow over Cylinder 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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5 More Metal Cutting Tools Calculators
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Verified Radiative Heat Transfer to Surface Stemming from Thermal Radiation
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1 More Modern Design Oriented Code Calculators
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Verified Radius of Cylinder for Non-Lifting Flow
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Verified Stream Function for Non-Lifting Flow over Circular Cylinder
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8 More Nonlifting Flow over Cylinder Calculators
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Created Characteristic Mach Number
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Created Downstream Velocity using Prandtl Relation
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Created Relation between Mach Number and Characteristic Mach Number
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4 More Normal Shock Relations 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 due to Oblique Shock
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7 More Oblique Shock 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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Created Friction Coefficient
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20 More Others and Extra Calculators
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Verified Coefficient of Drag Equation using Energy Released from Blast Wave
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7 More Planar and Blunt Slab Blast Wave Calculators
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Created Power required at Altitude
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Created Power required at Altitude given Power at sea-level
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Created Power required at sea-level conditions
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Created Velocity at Altitude
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Created Velocity at Altitude given Velocity at Sea-Level
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Created Velocity at Sea-Level given Lift Coefficient
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11 More Preliminary Aerodynamics Calculators
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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 Bend in Pipe
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Verified Loss of head due to sudden enlargement at any particular section of pipe
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11 More Pressure and Flow Head Calculators
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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 Power Available for Reciprocating Engine-Propeller Combination
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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 Propeller Efficiency for Reciprocating Engine-Propeller Combination
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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 Shaft Brake Power for Reciprocating Engine-Propeller Combination
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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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9 More Propeller Driven Airplane Calculators
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Verified Density Ratio across Normal Shock
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Created Entropy Change across Normal Shock
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Verified Pressure Ratio across Normal Shock
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Created Shock Strength
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2 More Property Change Across Shock Waves Calculators
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Created Load Factor given Pull-Down Maneuver Radius
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Created Load Factor given Pull-Down Maneuver Rate
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Created Load Factor given Pull-UP Maneuver Radius
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Created Load Factor 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 given Pull-Down Maneuver Rate
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Created Velocity for given Pull-Up Maneuver Radius
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Created Velocity for given Turn Rate for High Load Factor
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Created Velocity given Pull-down Maneuver Radius
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Verified Local Turbulent Skin-Friction Coefficient for Incompressible Flow
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Verified Reynolds Number for Chord Length using 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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Verified Area of Plane Wall Required for Given Temperature Difference
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Verified Outer Surface Temperature of Wall in Conduction through Wall
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Verified Thermal Conductivity of Material Required to Maintain Given Temperature Difference
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Verified Thickness of Plane Wall for Conduction through Wall
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4 More Single Plane Wall Calculators
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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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4 More Source Flow Calculators
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Created Control stick length for given gearing ratio
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Created Elevator Area given Hinge Moment Coefficient
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Created Elevator Area given Stick Force
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Created Elevator Chord Length given Hinge Moment Coefficient
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Created Elevator Chord Length given Stick Force
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Created Elevator Deflection Angle for given Stick Force
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Created Elevator Deflection Angle given Gearing Ratio
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Created Elevator Hinge moment coefficient
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Created Elevator Hinge Moment given Hinge Moment Coefficient
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Created Elevator Stick Force
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Created Elevator Stick Force given Gearing Ratio
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Created Elevator Stick Force given Hinge Moment Coefficient
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Created Flight Velocity for given Stick Force
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Created Flight Velocity given Elevator Hinge Moment Coefficient
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Created Gearing Ratio
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Created Gearing Ratio for given Stick Force
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Created Gearing Ratio given Hinge Moment Coefficient
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Created Hinge Moment Coefficient 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 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 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 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 Tail Volume Ratio
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Created Tail Lift for given Tail Pitching Moment
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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
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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 Tail Pitching Moment for given Lift Coefficient
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Created Tail Pitching Moment for given Moment Coefficient
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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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1 More Take Off Calculators
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Created Mach Angle
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Created Mach Number
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Created Speed of Sound
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Created Stagnation Temperature
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15 More Thermodynamics and Governing Equations Calculators
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Created Minimum Thrust of aircraft 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 Power required for given aerodynamic coefficients
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Created Power required for given required thrust of aircraft
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Created Power required for given total drag force
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Created Thrust Angle for Unaccelerated Level Flight for given Drag
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Created Thrust Angle for Unaccelerated Level Flight for given Lift
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Created Thrust for given coefficients of lift and drag
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Created Thrust for Level and Unaccelerated Flight
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Created Thrust of aircraft required for given Lift-to-drag ratio
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Created Thrust of Aircraft required for given required Power
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Created Thrust of Aircraft required for Level, Unaccelerated Flight
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Created Thrust-to-weight ratio
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Created Weight of Aircraft for given Coefficients of Lift and Drag
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Created Weight of Aircraft for given Lift-to-Drag Ratio
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Created Weight of aircraft for given required power
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Created Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle
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Created Weight of Aircraft in Level, Unaccelerated Flight
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Verified Discharge through Pipe given Head Loss in Turbulent Flow
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Verified Head Loss due to Friction given Power Required in Turbulent Flow
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16 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 given Load Factor
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Created Load factor given Lift Force and Weight of Aircraft
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Created Load Factor given Turn Radius
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Created Load Factor given Turn Rate
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Created Turn radius
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Created Turn rate
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Created Velocity for given turn radius
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Created Velocity for given turn rate
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Created Weight for given Load Factor
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Created Weight of aircraft during level turn
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1 More Turning Flight Calculators
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Verified Velocity Potential for Uniform Incompressible Flow
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3 More Uniform Flow Calculators
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Verified Density ahead of Normal Shock using Normal Shock Momentum Equation
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Verified Static Pressure ahead 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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4 More Upstream Shock Waves Calculators
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Verified Coefficient of Velocity given Head Loss
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Verified Theoretical velocity
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Verified Time of Emptying Circular Horizontal Tank
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5 More Velocity and Time 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 Moment Coefficient
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Created Moment Produced by Vertical Tail for given Side Force
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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 Moment
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Created Vertical Tail Area for given Vertical Tail Side Force
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Created Vertical tail area for given vertical tail volume ratio
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Created Vertical Tail Area for given Yawing Moment Coefficient
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Created Vertical Tail Dynamic Pressure for given Vertical Tail Side Force
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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
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Created Vertical Tail Lift Curve Slope for Given Moment
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Created Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency
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Created Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient
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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 Moment Arm for given Vertical Tail Volume Ratio
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Created Vertical Tail Moment Arm for Given Yawing Moment Coefficient
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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 Vertical tail volume ratio
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Created Vertical Tail Volume Ratio for given Yawing Moment Coefficient
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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 Viscous Flow Calculators
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Verified Velocity Potential for 2-D Vortex Flow
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2 More Vortex Flow Calculators
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Verified Wall Temperature over Flat Plate under Viscous, Very High Mach Flow
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3 More Wall Temperature Calculators
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Created Angle of Attack at Tail
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Created Angle of Attack of 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 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 for given Pitching Moment Coefficient
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Created Tail Lift Coefficient of Wing-Tail Combination
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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 Wing Lift Coefficient of wing-tail combination
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Created Dynamic Pressure at Vertical Tail for given Vertical Tail Efficiency
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Created Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient
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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 Dynamic Pressure for given Moment
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Created Wing Area for given Moment Produced by Vertical Tail
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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 Wing Dynamic Pressure 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
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Created Wingspan for Yawing Moment Coefficient given Sideslip Angle and Sidewash Angle
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