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Calculators Created by Vinay Mishra
Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology
(IIAEIT)
,
Pune
https://www.linkedin.com/in/imvk93/
338
Formulas Created
141
Formulas Verified
88
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 88 different categories till date.
2 Layers
(4)
Verified
Heat Flow Rate through Composite Wall of 2 Layers in Series
Go
Verified
Interface Temperature of Composite Wall of 2 Layers given Inner Surface Temperature
Go
Verified
Length of 2nd Layer of Composite Wall in Conduction through Walls
Go
Verified
Outer Surface Temperature of Composite Wall of 2 Layers for Conduction
Go
4 More 2 Layers Calculators
Go
3 Layers
(2)
Verified
Heat Flow Rate through Composite Wall of 3 Layers in Series
Go
Verified
Outer Surface Temperature of Composite Wall of 3 Layers for Conduction
Go
4 More 3 Layers Calculators
Go
Aerodynamic Measurements and Wind Tunnel Testing
(3)
Verified
Height Difference of Manometric Fluid for given Pressure Difference
Go
Verified
Surface Pressure on Body using Pressure Coefficient
Go
Verified
Wind Tunnel Pressure Difference with Test Speed
Go
7 More Aerodynamic Measurements and Wind Tunnel Testing Calculators
Go
Aerodynamic Parameters
(10)
Created
Sideslip angle for Aircraft
Go
Created
Sideslip angle for given moment produced by vertical tail
Go
Created
Sideslip angle for yawing moment coefficient given vertical tail volume ratio
Go
Created
Sidewash angle
Go
Created
Sidewash angle for given moment produced by vertical tail
Go
Created
Sidewash angle for given yawing moment coefficient
Go
Created
Sidewash Angle given Yawing Moment Coefficient using Wingspan
Go
Created
Yawing moment coefficient for given vertical tail lift curve slope
Go
Created
Yawing moment coefficient for given vertical tail volume ratio
Go
Created
Yawing Moment Coefficient using Wingspan
Go
Aircraft Dynamics Nomenclature
(17)
Created
Aerodynamic axial force
Go
Created
Aerodynamic normal force
Go
Created
Aerodynamic side force
Go
Created
Angle of attack
Go
Created
Normal force coefficient with aerodynamic normal force
Go
Created
Pitching moment
Go
Created
Pitching moment coefficient
Go
Created
Rolling moment
Go
Created
Rolling moment coefficient
Go
Created
Side force coefficient
Go
Created
Sideslip angle
Go
Created
Velocity along pitch axis for small sideslip angle
Go
Created
Velocity along roll axis for small angle of attack
Go
Created
Velocity along roll axis for small sideslip angle
Go
Created
Velocity along yaw axis for small angle of attack
Go
Created
Yawing moment
Go
Created
Yawing moment coefficient
Go
1 More Aircraft Dynamics Nomenclature Calculators
Go
Approximate Results Applied to Hypersonic Vehicles
(4)
Verified
Adiabatic Wall Enthalpy over Flat Plate using Stanton Number
Go
Verified
Freestream Density over Flat Plate using Stanton Number
Go
Verified
Freestream Velocity over Flat Plate using Stanton Number
Go
Verified
Wall Enthalpy over Flat Plate using Stanton Number
Go
11 More Approximate Results Applied to Hypersonic Vehicles Calculators
Go
Atmosphere and Gas Properties
(5)
Created
Absolute altitude
Go
Created
Geometric altitude
Go
Created
Geometric altitude for given geopotential altitude
Go
Created
Geopotential altitude
Go
Created
Lapse rate
Go
9 More Atmosphere and Gas Properties Calculators
Go
Basics of HMT
(3)
Verified
Thermal resistance for conduction through 2 resistances in parallel
Go
Verified
Total Thermal Resistance for Conduction through Three Resistances in Series
Go
Verified
Total Thermal Resistance for Conduction through Two Resistances in Series
Go
3 More Basics of HMT Calculators
Go
Bernoulli's Equation and Pressure Concepts
(2)
Verified
Pressure at Downstream Point by Bernoulli's Equation
Go
Verified
Velocity at Point on Airfoil for given Pressure Coefficient and Free-Stream Velocity
Go
4 More Bernoulli's Equation and Pressure Concepts Calculators
Go
Blast Wave Part Theory
(2)
Verified
Pressure Coefficient for Blast Wave Theory at Very High Values of Mach
Go
Verified
Pressure Coefficient for Blunt-Nosed Plate
Go
4 More Blast Wave Part Theory Calculators
Go
Body Lying on Rough Horizontal Plane
(2)
Created
Acceleration of System with Bodies One Hanging Free and Other Lying on Rough Horizontal Plane
Go
Created
Tension in String given Coefficient of Friction of Horizontal Plane
Go
Body Lying on Rough Inclined Plane
(7)
Created
Acceleration of System with Bodies One Hanging Free, Other Lying on Rough Inclined Plane
Go
Created
Coefficient of Friction given Frictional Force
Go
Created
Coefficient of Friction given Tension
Go
Created
Frictional Force
Go
Created
Inclination of Plane for given Frictional Force
Go
Created
Mass of Body B given Frictional Force
Go
Created
Tension in String given Coefficient of Friction of Inclined Plane
Go
Body Lying on Rough Inclined Plane
(6)
Created
Acceleration of System given Mass of Body A
Go
Created
Acceleration of System given Mass of Body B
Go
Created
Frictional Force on Body A
Go
Created
Frictional Force on Body B
Go
Created
Tension in String given Mass of Body A
Go
Created
Tension in String given Mass of Body B
Go
Body Lying on Smooth Horizontal Plane
(2)
Created
Acceleration in System
Go
Created
Tension in String if only One Body is Freely Suspended
Go
Body Lying on Smooth Inclined Plane
(4)
Created
Acceleration of System with Bodies One Hanging Free and Other Lying on Smooth Inclined Plane
Go
Created
Angle of Inclination given Acceleration
Go
Created
Angle of Inclination given Tension
Go
Created
Tension in String when One Body is Lying on Smooth Inclined Plane
Go
Body Lying on Smooth Inclined Plane
(4)
Created
Acceleration of System with Bodies Connected by String and Lying on Smooth Inclined Planes
Go
Created
Angle of Inclination of Plane with Body A
Go
Created
Angle of Inclination of Plane with Body B
Go
Created
Tension in String if Both Bodies are Lying on Smooth Inclined Planes
Go
Body Passing Over Smooth Pulley
(3)
Created
Acceleration of Bodies
Go
Created
Mass of Body B of Smaller Mass
Go
Created
Tension in String if Both Bodies are Freely Hanging
Go
Boundary Layer Flow
(5)
Verified
Average Coefficient of Drag for Drag Force
Go
Verified
Drag Force for Average Drag Coefficient
Go
Verified
Freestream Velocity for Local Drag Coefficient
Go
Verified
Local Drag Coefficient for Shear Stress
Go
Verified
Shear Stress for Local Drag Coefficient
Go
16 More Boundary Layer Flow Calculators
Go
Buoyancy
(4)
Verified
Centre of Buoyancy
Go
Verified
Meta-centric height for time period of oscillation and radius of gyration
Go
Verified
Radius of gyration for metacentric height and time period of oscillation
Go
Verified
Volume of fluid displaced
Go
7 More Buoyancy Calculators
Go
Climbing Flight
(15)
Created
Centrifugal Force in Accelerated Flight
Go
Created
Drag in Accelerated Flight
Go
Created
Excess power
Go
Created
Excess power for given rate of climb
Go
Created
Flight path angle at given rate of climb
Go
Created
Lift in Accelerated Flight
Go
Created
Rate of Climb
Go
Created
Rate of Climb for given excess power
Go
Created
Thrust available for given excess power
Go
Created
Thrust in Accelerated Flight
Go
Created
Total Drag for given excess power
Go
Created
Velocity in Accelerated Flight
Go
Created
Velocity of aircraft at given rate of climb
Go
Created
Velocity of aircraft for given excess power
Go
Created
Weight of aircraft for given excess power
Go
1 More Climbing Flight Calculators
Go
Compressible Flow Parameters
(2)
Verified
Bulk Modulus for Velocity of Sound Wave
Go
Verified
Velocity of Sound Wave given Bulk Modulus
Go
8 More Compressible Flow Parameters Calculators
Go
Conduction in Cylinder
(8)
Verified
Heat Flow Rate through Cylindrical Composite Wall of 2 Layers
Go
Verified
Heat Flow Rate through Cylindrical Composite Wall of 3 Layers
Go
Verified
Heat Flow Rate through Cylindrical Wall
Go
Verified
Inner Surface Temperature of Cylindrical Wall in Conduction
Go
Verified
Outer Surface Temperature of Cylindrical Composite Wall of 2 Layers
Go
Verified
Outer Surface Temperature of Cylindrical Wall given Heat Flow Rate
Go
Verified
Thermal Conductivity of Cylindrical Wall given Temperature Difference
Go
Verified
Thermal Resistance for Radial Heat Conduction in Cylinders
Go
6 More Conduction in Cylinder Calculators
Go
Conduction in Plane Wall
(4)
Verified
Area of Plane Wall Required for Given Temperature Difference
Go
Verified
Outer Surface Temperature of Wall in Conduction through Wall
Go
Verified
Thermal Conductivity of Material Required to Maintain Given Temperature Difference
Go
Verified
Thickness of Plane Wall for Conduction through Wall
Go
4 More Conduction in Plane Wall Calculators
Go
Cylinder Properties
(2)
Verified
Circulation for Lift Force on Cylinder
Go
Verified
Length of Cylinder for Lift Force on Cylinder
Go
5 More Cylinder Properties Calculators
Go
Cylindrical Blast Wave
(1)
Verified
Modified Energy for Cylindrical Blast Wave
Go
7 More Cylindrical Blast Wave Calculators
Go
Dimensionless Quantities
(1)
Verified
Stanton Number with Reynolds Number, Nusselt's Number, Stanton Number and Prandtl Number
Go
3 More Dimensionless Quantities Calculators
Go
Dimensions and Geometry
(1)
Verified
Diameter of Sphere in Falling Sphere Resistance Method
Go
18 More Dimensions and Geometry Calculators
Go
Discharge
(5)
Verified
Discharge over Broad-Crested Weir
Go
Verified
Discharge over Rectangle Notch or Weir
Go
Verified
Discharge over Rectangle Weir for Bazin's formula with Velocity of Approach
Go
Verified
Discharge over Rectangle Weir with Two End Contractions
Go
Verified
Head of Liquid at Crest
Go
12 More Discharge Calculators
Go
Downstream Shock Waves
(7)
Created
Characteristic Mach Number behind Shock
Go
Verified
Density behind Normal Shock using Normal Shock Momentum Equation
Go
Created
Mach Number behind Shock
Go
Verified
Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula
Go
Verified
Static Pressure behind Normal Shock using Normal Shock Momentum Equation
Go
Created
Velocity behind Normal Shock
Go
Verified
Velocity behind Normal Shock from Normal Shock Energy Equation
Go
8 More Downstream Shock Waves Calculators
Go
Expansion Waves
(5)
Verified
Prandtl Meyer Function
Go
Verified
Prandtl Meyer Function at Upstream Mach Number
Go
Verified
Pressure behind Expansion Fan
Go
Verified
Rearward Mach Angle of Expansion Fan
Go
Verified
Temperature behind Expansion Fan
Go
5 More Expansion Waves Calculators
Go
Flow Analysis
(1)
Verified
Viscosity of Fluid or Oil in Falling Sphere Resistance Method
Go
12 More Flow Analysis Calculators
Go
Flow Head
(2)
Verified
Head of liquid for head loss and coefficient of velocity
Go
Verified
Loss of head due to fluid resistance
Go
4 More Flow Head Calculators
Go
Flow over Airfoils
(1)
Verified
Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory
Go
7 More Flow over Airfoils Calculators
Go
Flow Rate
(4)
Verified
Coefficient of Discharge given Time of Emptying Circular Horizontal Tank
Go
Verified
Discharge through fully sub-merged orifice
Go
Verified
Discharge through large rectangular orifice
Go
Verified
Discharge through partially sub-merged orifice
Go
7 More Flow Rate Calculators
Go
Flow Regime
(3)
Verified
Time required to close Valve for Gradual Closure of Valves
Go
Verified
Velocity at section 1-1 for sudden enlargement
Go
Verified
Velocity at section 2-2 for sudden enlargement
Go
14 More Flow Regime Calculators
Go
Fluid Flow and Resistance
(4)
Verified
Buoyant Force in Falling Sphere Resistance Method
Go
Verified
Density of Fluid in Falling Sphere Resistance Method
Go
Verified
Drag Force in Falling Sphere Resistance Method
Go
Verified
Velocity of Sphere in Falling Sphere Resistance Method
Go
17 More Fluid Flow and Resistance Calculators
Go
Fluid Parameters and Characteristics
(2)
Verified
Freestream Velocity for Lift Coefficient in Rotating Cylinder with Circulation
Go
Verified
Freestream velocity for lift coefficient with tangential speed
Go
7 More Fluid Parameters and Characteristics Calculators
Go
Force Normal to Shear
(1)
Created
Cutting Shear Force given Uncut Chip Thickness and Shear Angle
Go
3 More Force Normal to Shear Calculators
Go
Forces and Friction
(1)
Created
Shear force acting on shear plane for given shear stress and area of shear plane
Go
5 More Forces and Friction Calculators
Go
Geometric DImension
(3)
Verified
Length of Section for Discharge over Rectangle Notch or Weir
Go
Verified
Length of Weir Considering Bazin's formula with Velocity of Approach
Go
Verified
Length of Weir for Discharge over Broad-Crested Weir
Go
7 More Geometric DImension Calculators
Go
Geometry and Dimensions
(3)
Created
Shear angle for given area of shear plane, width of cut and uncut chip thickness
Go
Created
Uncut chip thickness for given width of cut, shear angle and area of shear plane
Go
Created
Width of cut for given shear angle, uncut chip thickness and area of shear plane
Go
5 More Geometry and Dimensions Calculators
Go
Gibbs Phase Rule
(4)
Created
Degree of Freedom
Go
Created
Number of Components
Go
Created
Number of Phases
Go
Created
Total Number of Variables in System
Go
Gliding Flight
(5)
Created
Drag for given Glide Angle
Go
Created
Glide angle
Go
Created
Glide angle for given lift-to-drag ratio
Go
Created
Lift Force for given Glide Angle
Go
Created
Lift-to-drag ratio for given glide angle
Go
1 More Gliding Flight Calculators
Go
Governing Equations and Sound Wave
(8)
Verified
Critical Density
Go
Verified
Critical Pressure
Go
Verified
Critical Temperature
Go
Verified
Isentropic Compressibility for given Density and Speed of Sound
Go
Created
Mayer's Formula
Go
Created
Ratio of Stagnation and Static Density
Go
Created
Ratio of Stagnation and Static Pressure
Go
Created
Ratio of Stagnation and Static Temperature
Go
10 More Governing Equations and Sound Wave Calculators
Go
High Load Factor Maneuver
(27)
Created
Lift Coefficient for given Turn Radius
Go
Created
Lift Coefficient for given turn rate
Go
Created
Lift Coefficient for given wing loading and turn radius
Go
Created
Load factor for given turn radius for high-performance fighter aircraft
Go
Created
Load factor for given turn rate for high-performance fighter aircraft
Go
Created
Load Factor given Pull-down Maneuver Radius
Go
Created
Load Factor given Pull-down Maneuver Rate
Go
Created
Load Factor given Pull-UP Maneuver Radius
Go
Created
Load Factor given Pull-Up Maneuver Rate
Go
Created
Pull-down maneuver radius
Go
Created
Pull-down maneuver rate
Go
Created
Pull-up maneuver radius
Go
Created
Pull-up maneuver rate
Go
Created
Radius of turn for given lift coefficient
Go
Created
Radius of turn for given wing loading
Go
Created
Turn radius for high load factor
Go
Created
Turn rate for given lift coefficient
Go
Created
Turn rate for given wing loading
Go
Created
Turn rate for high load factor
Go
Created
Velocity for given pull-down maneuver rate
Go
Created
Velocity for given pull-up maneuver radius
Go
Created
Velocity for given pull-up maneuver rate
Go
Created
Velocity for given turn rate for high load factor
Go
Created
Velocity given Pull-down Maneuver Radius
Go
Created
Velocity given Turn Radius for High Load Factor
Go
Created
Wing loading for given turn radius
Go
Created
Wing loading for given turn rate
Go
2 More High Load Factor Maneuver Calculators
Go
Hypersonic Flow Parameters
(2)
Verified
Axial Force Coefficient
Go
Verified
Normal Force Coefficient
Go
18 More Hypersonic Flow Parameters Calculators
Go
Hypersonic Flow Parameters
(1)
Verified
Local Skin-Friction Coefficient
Go
6 More Hypersonic Flow Parameters Calculators
Go
Hypersonic Transition
(3)
Verified
Reynolds Number Equation using Boundary-Layer Momentum Thickness
Go
Verified
Reynolds Number Equation using Local Mach Number
Go
Verified
Thermal Conductivity of Transition Flow
Go
13 More Hypersonic Transition Calculators
Go
Incompressible Flow Characteristics
(8)
Verified
Radial velocity at any radius
Go
Verified
Radius at any point considering radial velocity
Go
Verified
Stream function at point
Go
Verified
Stream Function at Point in Combined Flow
Go
Verified
Stream function in sink flow for angle
Go
Verified
Strength of doublet for stream function
Go
Verified
Strength of source for radial velocity and at any radius
Go
Verified
Uniform flow velocity for stream function at point in combined flow
Go
15 More Incompressible Flow Characteristics Calculators
Go
Jet Airplane
(8)
Created
Endurance for given Lift-to-Drag ratio of Jet Airplane
Go
Created
Endurance of Jet Airplane
Go
Created
Lift-to-Drag ratio for given Endurance of Jet Airplane
Go
Created
Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
Go
Created
Range of Jet Airplane
Go
Created
Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
Go
Created
Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane
Go
Created
Thrust-Specific Fuel Consumption for given Range of Jet Airplane
Go
10 More Jet Airplane Calculators
Go
Kutta-Joukowski Lift Theorem
(1)
Verified
Circulation by Kutta-Joukowski Theorem
Go
3 More Kutta-Joukowski Lift Theorem Calculators
Go
Laminar Boundary Layer at Stagnation point on Blunt body
(2)
Verified
Reynolds Analogy Factor in Finite Deference Method
Go
Verified
Reynolds Analogy for Stanton Number in Finite Difference Method
Go
5 More Laminar Boundary Layer at Stagnation point on Blunt body Calculators
Go
Landing
(4)
Created
Landing ground roll distance
Go
Created
Stall velocity for given touchdown velocity
Go
Created
Touchdown velocity
Go
Created
Touchdown velocity for given stall velocity
Go
1 More Landing Calculators
Go
Lateral Stability
(5)
Created
Aircraft forward velocity for given normal component of side velocity
Go
Created
Aircraft sideslip velocity for given dihedral angle
Go
Created
Dihedral angle for given sideslip velocity
Go
Created
Normal component of aircraft side velocity for given dihedral angle
Go
Created
Normal component of aircraft side velocity for given forward velocity
Go
Lift and Circulation
(5)
Verified
Lift Coefficient for Rotating Cylinder with Circulation
Go
Verified
Lift Coefficient for Rotating Cylinder with Tangential Speed
Go
Verified
Lift Force on Cylinder for Circulation
Go
Verified
Radius of Cylinder for Lift Coefficient in Rotating Cylinder with Circulation
Go
Verified
Tangential Velocity of Cylinder with Lift Coefficient
Go
11 More Lift and Circulation Calculators
Go
Lift and Drag Polar
(4)
Created
Coefficient of Drag due to lift
Go
Created
Drag Coefficient for given parasite drag coefficient
Go
Created
Drag Coefficient for given zero-lift drag coefficient
Go
Created
Parasite Drag Coefficient at zero lift
Go
17 More Lift and Drag Polar Calculators
Go
Lift and Drag Requirements
(19)
Created
Coefficient of Drag due to lift for minimum power required
Go
Created
Coefficient of Drag for given thrust and weight
Go
Created
Coefficient of Drag for given thrust-to-weight ratio
Go
Created
Coefficient of Lift for given thrust and weight
Go
Created
Coefficient of Lift for given thrust-to-weight ratio
Go
Created
Drag for Level and Unaccelerated Flight
Go
Created
Drag for Level and Unaccelerated Flight at Negligible Thrust Angle
Go
Created
Freestream velocity for given required power
Go
Created
Freestream Velocity for given total drag force
Go
Created
Lift coefficient for given minimum required thrust
Go
Created
Lift for Level and Unaccelerated Flight at Negligible Thrust Angle
Go
Created
Lift for Unaccelerated Flight
Go
Created
Lift-induced drag coefficient for given required thrust
Go
Created
Lift-to-drag ratio for given required thrust of aircraft
Go
Created
Total drag force for given required power
Go
Created
Zero-lift drag coefficient at minimum required thrust
Go
Created
Zero-lift drag coefficient for given lift coefficient
Go
Created
Zero-lift drag coefficient for given required thrust
Go
Created
Zero-lift drag coefficient for minimum power required
Go
Lifting Flow over Cylinder
(3)
Verified
Location of Stagnation Point Outside Cylinder for Lifting Flow
Go
Verified
Radial Velocity for Lifting Flow over Circular Cylinder
Go
Verified
Surface Pressure Coefficient for Lifting Flow over Circular Cylinder
Go
7 More Lifting Flow over Cylinder Calculators
Go
Metal Cutting Tools
(4)
Created
Back Rake Angle
Go
Created
Inclination Angle
Go
Created
Orthogonal Rake Angle
Go
Created
Side Rake Angle
Go
5 More Metal Cutting Tools Calculators
Go
Modern Design Oriented Code
(1)
Verified
Radiative Heat Transfer to Surface Stemming from Thermal Radiation
Go
1 More Modern Design Oriented Code Calculators
Go
Nonlifting Flow over Cylinder
(2)
Verified
Radius of Cylinder for Non-Lifting Flow
Go
Verified
Stream Function for Non-Lifting Flow over Circular Cylinder
Go
8 More Nonlifting Flow over Cylinder Calculators
Go
Normal Shock Relations
(3)
Created
Characteristic Mach Number
Go
Created
Downstream Velocity using Prandtl Relation
Go
Created
Relation between Mach Number and Characteristic Mach Number
Go
4 More Normal Shock Relations Calculators
Go
Oblique Shock
(3)
Created
Component of Downstream Mach Normal to Oblique Shock
Go
Created
Component of Upstream Mach Normal to Oblique Shock
Go
Created
Flow Deflection Angle due to Oblique Shock
Go
7 More Oblique Shock Calculators
Go
Oblique Shock Relation
(2)
Created
Dynamic Pressure for given Specific Heat Ratio and Mach Number
Go
Verified
Velocity of Sound using Dynamic Pressure and Density
Go
13 More Oblique Shock Relation Calculators
Go
Others & Extra
(1)
Created
Friction Coefficient
Go
4 More Others & Extra Calculators
Go
Planar and Blunt Slab Blast Wave
(1)
Verified
Coefficient of Drag Equation using Energy Released from Blast Wave
Go
7 More Planar and Blunt Slab Blast Wave Calculators
Go
Preliminary Aerodynamics
(6)
Created
Power required at Altitude
Go
Created
Power required at Altitude given Power at sea-level
Go
Created
Power required at sea-level conditions
Go
Created
Velocity at Altitude
Go
Created
Velocity at Altitude given Velocity at Sea-Level
Go
Created
Velocity at Sea-level given Lift Coefficient
Go
11 More Preliminary Aerodynamics Calculators
Go
Pressure and Flow Head
(3)
Verified
Intensity of pressure wave produced for gradual closure of valves
Go
Verified
Loss of Head due to Bend in Pipe
Go
Verified
Loss of head due to sudden enlargement at any particular section of pipe
Go
11 More Pressure and Flow Head Calculators
Go
Propeller-Driven Airplane
(12)
Created
Endurance of Propeller-Driven Airplane
Go
Created
Power available for reciprocating engine-propeller combination
Go
Created
Propeller Efficiency for given Endurance of Propeller-Driven Airplane
Go
Created
Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go
Created
Propeller Efficiency for given Range of Propeller-Driven Airplane
Go
Created
Propeller efficiency for reciprocating engine-propeller combination
Go
Created
Range of Propeller-Driven Airplane
Go
Created
Range of Propeller-Driven Airplane for given lift-to-drag ratio
Go
Created
Shaft brake power for reciprocating engine-propeller combination
Go
Created
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
Go
Created
Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go
Created
Specific Fuel Consumption for given Range of Propeller-Driven Airplane
Go
9 More Propeller-Driven Airplane Calculators
Go
Property Change Across Shock Waves
(4)
Verified
Density Ratio across Normal Shock
Go
Created
Entropy Change across Normal Shock
Go
Verified
Pressure Ratio across Normal Shock
Go
Created
Shock Strength
Go
2 More Property Change Across Shock Waves Calculators
Go
Reference Temperature Method
(3)
Verified
Local Turbulent Skin-Friction Coefficient for Incompressible Flow
Go
Verified
Reynolds Number for Chord Length using Overall Skin-Friction Drag Coefficient
Go
Verified
Turbulent Flat-Plate Skin-Friction Coefficient
Go
12 More Reference Temperature Method Calculators
Go
Source Flow
(3)
Verified
Source Strength for 2-D Incompressible Source Flow
Go
Verified
Stagnation Streamline Equation for Flow over Semi-Infinite Body
Go
Verified
Stream Function for 2-D Incompressible Source Flow
Go
4 More Source Flow Calculators
Go
Stick Forces and Hinge Moments
(23)
Created
Control stick length for given gearing ratio
Go
Created
Elevator Area given Hinge Moment Coefficient
Go
Created
Elevator Area given Stick Force
Go
Created
Elevator Chord Length given Hinge Moment Coefficient
Go
Created
Elevator Chord Length given Stick Force
Go
Created
Elevator deflection angle for given stick force
Go
Created
Elevator Deflection Angle given Gearing Ratio
Go
Created
Elevator Hinge moment coefficient
Go
Created
Elevator Hinge Moment given Hinge Moment Coefficient
Go
Created
Elevator Stick Force
Go
Created
Elevator Stick Force given Gearing Ratio
Go
Created
Elevator Stick Force Given Hinge Moment Coefficient
Go
Created
Flight velocity for given stick force
Go
Created
Flight Velocity given Elevator Hinge Moment Coefficient
Go
Created
Gearing ratio
Go
Created
Gearing ratio for given stick force
Go
Created
Gearing Ratio given Hinge Moment Coefficient
Go
Created
Hinge Moment Coefficient given Stick Force
Go
Created
Hinge moment for given gearing ratio
Go
Created
Hinge moment for given stick force
Go
Created
Stick deflection angle for given gearing ratio
Go
Created
Stick deflection angle for given stick force
Go
Created
Stick length for given stick force
Go
Tail Contribution
(19)
Created
Horizontal tail area for given tail volume ratio
Go
Created
Horizontal tail volume ratio
Go
Created
Horizontal tail volume ratio for given pitching moment coefficient
Go
Created
Mean aerodynamic chord for given tail pitching moment coefficient
Go
Created
Pitching moment due to tail
Go
Created
Tail area for given tail moment coefficient
Go
Created
Tail Efficiency for given pitching moment coefficient
Go
Created
Tail Efficiency for given tail volume ratio
Go
Created
Tail lift coefficient for given tail volume ratio
Go
Created
Tail lift for given tail pitching moment
Go
Created
Tail moment arm for given horizontal tail volume ratio
Go
Created
Tail moment arm for given tail moment coefficient
Go
Created
Tail Pitching moment coefficient
Go
Created
Tail Pitching moment coefficient for given tail efficiency
Go
Created
Tail Pitching moment coefficient for given tail volume ratio
Go
Created
Tail Pitching moment for given lift coefficient
Go
Created
Tail Pitching moment for given moment coefficient
Go
Created
Wing Mean aerodynamic chord for given horizontal tail volume ratio
Go
Created
Wing Reference area for given horizontal tail volume ratio
Go
Take-Off
(14)
Created
Coefficient of rolling friction during ground roll
Go
Created
Drag during ground effect
Go
Created
Ground effect factor
Go
Created
Lift acting on aircraft during ground roll
Go
Created
Liftoff distance
Go
Created
Liftoff velocity for given stall velocity
Go
Created
Liftoff velocity for given weight
Go
Created
Maximum Lift coefficient for given liftoff velocity
Go
Created
Maximum Lift coefficient for given stall velocity
Go
Created
Resistance force during ground roll
Go
Created
Stall velocity for given liftoff velocity
Go
Created
Stall velocity for given weight
Go
Created
Thrust for given liftoff distance
Go
Created
Weight of aircraft during ground roll
Go
1 More Take-Off Calculators
Go
Thermodynamics and Governing Equations
(4)
Created
Mach Angle
Go
Created
Mach Number
Go
Created
Speed of Sound
Go
Created
Stagnation Temperature
Go
15 More Thermodynamics and Governing Equations Calculators
Go
Thrust and Power Requirements
(19)
Created
Minimum Thrust of aircraft required
Go
Created
Minimum Thrust required for given lift coefficient
Go
Created
Minimum Thrust required for given weight
Go
Created
Power required for given aerodynamic coefficients
Go
Created
Power required for given required thrust of aircraft
Go
Created
Power required for given total drag force
Go
Created
Thrust Angle for Unaccelerated Level Flight for given Drag
Go
Created
Thrust Angle for Unaccelerated Level Flight for given Lift
Go
Created
Thrust for given coefficients of lift and drag
Go
Created
Thrust for Level and Unaccelerated Flight
Go
Created
Thrust of aircraft required for given Lift-to-drag ratio
Go
Created
Thrust of aircraft required for given required power
Go
Created
Thrust of aircraft required for level, unaccelerated flight
Go
Created
Thrust-to-weight ratio
Go
Created
Weight of aircraft for given coefficients of lift and drag
Go
Created
Weight of aircraft for given Lift-to-drag ratio
Go
Created
Weight of aircraft for given required power
Go
Created
Weight of aircraft for level, unaccelerated flight at negligible thrust angle
Go
Created
Weight of aircraft in level, unaccelerated flight
Go
Turbulent Flow
(2)
Verified
Discharge through Pipe given Head Loss in Turbulent Flow
Go
Verified
Head Loss due to Friction given Power Required in Turbulent Flow
Go
16 More Turbulent Flow Calculators
Go
Turning Flight
(12)
Created
Bank angle during level turn
Go
Created
Lift during level turn
Go
Created
Lift for given load factor
Go
Created
Load factor given Lift Force and Weight of Aircraft
Go
Created
Load Factor given Turn Radius
Go
Created
Load Factor given Turn Rate
Go
Created
Turn radius
Go
Created
Turn rate
Go
Created
Velocity for given turn radius
Go
Created
Velocity for given turn rate
Go
Created
Weight for given Load Factor
Go
Created
Weight of aircraft during level turn
Go
1 More Turning Flight Calculators
Go
Uniform Flow
(1)
Verified
Velocity Potential for Uniform Incompressible Flow
Go
3 More Uniform Flow Calculators
Go
Upstream Shock Waves
(3)
Verified
Density ahead of Normal Shock using Normal Shock Momentum Equation
Go
Verified
Static Pressure ahead of Normal Shock using Normal Shock Momentum Equation
Go
Verified
Velocity ahead of Normal Shock from Normal Shock Energy Equation
Go
4 More Upstream Shock Waves Calculators
Go
Velocity and Time
(3)
Verified
Coefficient of Velocity given Head Loss
Go
Verified
Theoretical velocity
Go
Verified
Time of Emptying Circular Horizontal Tank
Go
5 More Velocity and Time Calculators
Go
Vertical Tail Contribution
(24)
Created
Moment produced by vertical tail for given lift curve slope
Go
Created
Moment produced by vertical tail for given moment coefficient
Go
Created
Moment produced by vertical tail for given side force
Go
Created
Vertical tail angle of attack
Go
Created
Vertical tail angle of attack for given vertical tail side force
Go
Created
Vertical tail area for given moment
Go
Created
Vertical tail area for given vertical tail side force
Go
Created
Vertical tail area for given vertical tail volume ratio
Go
Created
Vertical tail area for given yawing moment coefficient
Go
Created
Vertical tail dynamic pressure for given vertical tail side force
Go
Created
Vertical tail efficiency
Go
Created
Vertical tail efficiency for given yawing moment coefficient
Go
Created
Vertical tail lift curve slope
Go
Created
Vertical tail lift curve slope for given moment
Go
Created
Vertical tail lift curve slope for given yawing moment coefficient
Go
Created
Vertical tail lift curve slope for given yawing moment coefficient and Vertical Tail Efficiency
Go
Created
Vertical tail moment arm for given lift curve slope
Go
Created
Vertical tail moment arm for given side force
Go
Created
Vertical tail moment arm for given vertical tail volume ratio
Go
Created
Vertical tail moment arm for given yawing moment coefficient
Go
Created
Vertical tail Side force
Go
Created
Vertical tail side force for given moment
Go
Created
Vertical tail volume ratio
Go
Created
Vertical tail volume ratio for given yawing moment coefficient
Go
Viscous Flow
(3)
Verified
Recovery Factor Calculation using Prandtl Number
Go
Verified
Recovery Factor for Flat Plate with Viscous Flow
Go
Verified
Skin-Friction Drag Coefficient
Go
12 More Viscous Flow Calculators
Go
Vortex Flow
(1)
Verified
Velocity Potential for 2-D Vortex Flow
Go
2 More Vortex Flow Calculators
Go
Wall Temperature
(1)
Verified
Wall Temperature over Flat Plate under Viscous, Very High Mach Flow
Go
3 More Wall Temperature Calculators
Go
Wing-Tail Contribution
(15)
Created
Angle of Attack at Tail
Go
Created
Angle of attack of wing
Go
Created
Angle of incidence of tail
Go
Created
Angle of incidence of wing
Go
Created
Downwash angle
Go
Created
Lift due to tail only
Go
Created
Lift due to wing only
Go
Created
Tail area for given tail efficiency
Go
Created
Tail Efficiency for given lift coefficients
Go
Created
Tail lift coefficient for given pitching moment
Go
Created
Tail lift coefficient for given pitching moment coefficient
Go
Created
Tail Lift Coefficient of wing-tail combination
Go
Created
Total Lift Coefficient of wing-tail combination
Go
Created
Total Lift of wing-tail combination
Go
Created
Wing Lift Coefficient of wing-tail combination
Go
Wing-Tail Interaction
(13)
Created
Dynamic pressure at vertical tail for given vertical tail efficiency
Go
Created
Dynamic pressure at vertical tail for given yawing moment coefficient
Go
Created
Dynamic pressure at wing for given vertical tail efficiency
Go
Created
Dynamic pressure at wing for given yawing moment coefficient
Go
Created
Sideslip angle for given yawing moment coefficient
Go
Created
Vertical tail dynamic pressure for given moment
Go
Created
Wing area for given moment produced by vertical tail
Go
Created
Wing area for given vertical tail volume ratio
Go
Created
Wing area for given yawing moment coefficient
Go
Created
Wing dynamic pressure for given yawing moment coefficient
Go
Created
Wingspan for given vertical tail volume ratio
Go
Created
Wingspan for given yawing moment coefficient
Go
Created
Wingspan for yawing moment coefficient given sideslip angle and sidewash angle
Go
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