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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/
340
Formulas Created
143
Formulas Verified
72
Across Categories
List of Calculators by Vinay Mishra
Following is a combined list of all the calculators that have been created and verified by Vinay Mishra. Vinay Mishra has created 340 and verified 143 calculators across 72 different categories till date.
Aerodynamic Nomenclature
(18)
Created
Aerodynamic axial force
Go
Created
Aerodynamic normal force
Go
Created
Aerodynamic side force
Go
Created
Angle of attack
Go
Created
Axial force coefficient
Go
Created
Normal force coefficient
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
Altitude Effects on Power Required and Available
(6)
Created
Power required at an altitude
Go
Created
Power required at an altitude for given power required at sea-level condition
Go
Created
Power required at sea-level condition
Go
Created
Velocity at an altitude
Go
Created
Velocity at an altitude for given velocity at sea-level condition
Go
Created
Velocity at sea-level condition
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
Basic Compressible Flow
(6)
Verified
Critical Density
Go
Verified
Critical Pressure
Go
Verified
Critical Temperature
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
Basics
(7)
Verified
Isentropic compressibility for given density and speed of sound
Go
Created
Mach Angle
Go
Created
Mach Number
Go
Created
Mayer's formula
Go
Created
Speed of Sound
Go
Created
Stagnation Temperature
Go
Verified
Thermal resistance for conduction through 2 resistances in parallel
Go
Basics
(2)
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 Calculators
Go
Blast-wave part 2
(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 2 Calculators
Go
Bodies connected by a string - one hanging free, other lying on a rough horizontal plane
(2)
Created
Acceleration of the system
Go
Created
Tension in the string
Go
Bodies connected by a string - one hanging free, other lying on a rough inclined plane
(7)
Created
Acceleration of the system
Go
Created
Coefficient of friction for given frictional force
Go
Created
Coefficient of friction for given tension
Go
Created
Frictional force
Go
Created
Inclination of plane for given frictional force
Go
Created
Mass of body B for given frictional force
Go
Created
Tension in the string
Go
Bodies connected by a string - one hanging free, other lying on a smooth horizontal plane
(2)
Created
Acceleration in the system
Go
Created
Tension in the string
Go
Bodies connected by a string - one hanging free, other lying on a smooth inclined plane
(4)
Created
Acceleration of the system
Go
Created
Angle of inclination for given acceleration
Go
Created
Angle of inclination for given tension
Go
Created
Tension in the string
Go
Bodies connected by a string and lying on rough inclined planes
(6)
Created
Acceleration of the system for given mass of body A
Go
Created
Acceleration of the system for given mass of body B
Go
Created
Frictional force on body A
Go
Created
Frictional force on body B
Go
Created
Tension in the string for given mass of body A
Go
Created
Tension in the string for given mass of body B
Go
Bodies connected by a string and lying on smooth inclined planes
(4)
Created
Acceleration of the system
Go
Created
Angle of inclination of plane with body A
Go
Created
Angle of inclination of plane with body B
Go
Created
Tension in the string
Go
Bodies connected by a string and passing over a smooth pulley
(3)
Created
Acceleration of the bodies
Go
Created
Mass of body B (smaller mass)
Go
Created
Tension in the string
Go
Boundary layer flow
(5)
Verified
Average coefficient of drag for drag force in boundary layer flows
Go
Verified
Drag force for average drag coefficient in boundary layer flows
Go
Verified
Freestream velocity for local drag coefficient in boundary layer flows
Go
Verified
Local drag coefficient for shear stress in boundary layer flows
Go
Verified
Shear stress for local drag coefficient in boundary layer flows
Go
16 More Boundary layer flow Calculators
Go
Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions
(2)
Verified
Local skin-friction coefficient
Go
Verified
Stanton number with Reynolds number, Nusselt's number, Stanton number and Prandtl number
Go
18 More Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions 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
5 More Buoyancy Calculators
Go
Compressible flow
(2)
Verified
Bulk modulus for the velocity of sound wave
Go
Verified
Velocity of sound wave in terms of bulk modulus
Go
22 More Compressible flow Calculators
Go
Contribution of Aircraft Components (Part 1)
(15)
Created
Moment produced by vertical tail for given lift curve slope
Go
Created
Moment produced by vertical tail for given side force
Go
Created
Sideslip angle
Go
Created
Sideslip angle for given moment produced by vertical tail
Go
Created
Sidewash angle
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 vertical tail side force
Go
Created
Vertical tail dynamic pressure for given vertical tail side force
Go
Created
Vertical tail lift curve slope
Go
Created
Vertical tail lift curve slope for given moment
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 Side force
Go
Created
Vertical tail side force for given moment
Go
Contribution of Aircraft Components (Part 2)
(14)
Created
Dynamic pressure at vertical tail for given yawing moment coefficient
Go
Created
Moment produced by vertical tail for given moment coefficient
Go
Created
Sideslip angle for given yawing moment coefficient
Go
Created
Sidewash angle for given moment produced by vertical tail
Go
Created
Sidewash angle for given yawing moment coefficient
Go
Created
Vertical tail area for given moment
Go
Created
Vertical tail area for given yawing moment coefficient
Go
Created
Vertical tail dynamic pressure for given moment
Go
Created
Vertical tail lift curve slope for given yawing moment coefficient
Go
Created
Wing area for given moment produced by vertical tail
Go
Created
Wing dynamic pressure for given yawing moment coefficient
Go
Created
Wingspan for given yawing moment coefficient
Go
Created
Yawing moment coefficient
Go
Created
Yawing moment coefficient for given vertical tail lift curve slope
Go
Contribution of Aircraft Components (Part 3)
(15)
Created
Dynamic pressure at vertical tail for given vertical tail efficiency
Go
Created
Dynamic pressure at wing for given vertical tail efficiency
Go
Created
Dynamic pressure at wing for given yawing moment coefficient
Go
Created
Vertical tail area for given vertical tail volume ratio
Go
Created
Vertical tail efficiency
Go
Created
Vertical tail efficiency for given yawing moment coefficient
Go
Created
Vertical tail lift curve slope for given yawing moment coefficient
Go
Created
Vertical tail moment arm for given vertical tail volume ratio
Go
Created
Vertical tail volume ratio
Go
Created
Vertical tail volume ratio for given yawing moment coefficient
Go
Created
Wing area for given vertical tail volume ratio
Go
Created
Wing area for given yawing moment coefficient
Go
Created
Wingspan for given vertical tail volume ratio
Go
Created
Wingspan for given yawing moment coefficient
Go
Created
Yawing moment coefficient for given vertical tail volume ratio
Go
Contribution of Aircraft Components (Part 4)
(2)
Created
Sideslip angle for given yawing moment coefficient
Go
Created
Sidewash angle for given yawing moment coefficient
Go
Cylinders
(8)
Verified
Heat flow rate through a cylindrical composite wall of 2 layers
Go
Verified
Heat flow rate through a cylindrical composite wall of 3 layers
Go
Verified
Heat flow rate through a cylindrical wall
Go
Verified
Inner surface temperature of a cylindrical wall for a given heat flow rate
Go
Verified
Outer surface temperature of a cylindrical wall for a given heat flow rate
Go
Verified
Outer surface temperature of the cylindrical composite wall of 2 layers
Go
Verified
Thermal conductivity of a cylindrical wall for a given temperature difference
Go
Verified
Thermal resistance for radial heat conduction offered by a cylinder wall
Go
6 More Cylinders Calculators
Go
Drag during Level Unaccelerated Flight
(7)
Created
Coefficient of Drag for given thrust and weight
Go
Created
Coefficient of Drag for given thrust-to-weight ratio
Go
Created
Drag for a level, unaccelerated flight at negligible thrust angle
Go
Created
Lift-induced drag coefficient for given required thrust
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
Elevator Hinge Moment
(5)
Created
Elevator area for given hinge moment coefficient
Go
Created
Elevator chord length for given hinge moment coefficient
Go
Created
Elevator Hinge moment coefficient
Go
Created
Elevator Hinge moment for given hinge moment coefficient
Go
Created
Flight velocity for given elevator hinge moment coefficient
Go
Equations of Motion
(11)
Created
Centrifugal Force in an accelerated flight
Go
Created
Drag for a level, unaccelerated flight
Go
Created
Drag in an accelerated flight
Go
Created
Lift for an unaccelerated flight
Go
Created
Lift in an accelerated flight
Go
Created
Thrust angle for an unaccelerated flight for given drag
Go
Created
Thrust angle for an unaccelerated flight for given lift
Go
Created
Thrust for a level, unaccelerated flight
Go
Created
Thrust in an accelerated flight
Go
Created
Velocity in an accelerated flight
Go
Created
Weight of aircraft in level, unaccelerated flight
Go
Flat-Plate for Viscous flow case
(3)
Verified
Overall skin-friction drag Coefficient
Go
Verified
Recovery factor calculation using Prandtl number
Go
Verified
Recovery factor for flat plate with viscous flow
Go
12 More Flat-Plate for Viscous flow case Calculators
Go
Flight Envelope
(15)
Created
Lift Coefficient for a given turn radius
Go
Created
Lift Coefficient for a given turn rate
Go
Created
Lift Coefficient for a given wing loading and turn radius
Go
Created
Load factor for a given turn radius for a high-performance fighter aircraft
Go
Created
Load factor for a given turn rate for a high-performance fighter aircraft
Go
Created
Radius of turn for a given lift coefficient
Go
Created
Radius of turn for a given wing loading
Go
Created
Turn radius for a high load factor
Go
Created
Turn rate for a given lift coefficient
Go
Created
Turn rate for a given wing loading
Go
Created
Turn rate for a high load factor
Go
Created
Velocity for a given turn radius for a high load factor
Go
Created
Velocity for a given turn rate for a high load factor
Go
Created
Wing loading for a given turn radius
Go
Created
Wing loading for a given turn rate
Go
Flow through pipes
(6)
Verified
Intensity of pressure wave produced for gradual closure of valves
Go
Verified
Loss of head due to bead in a pipe
Go
Verified
Loss of head due to sudden enlargement
Go
Verified
Time required to close the 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
33 More Flow through pipes Calculators
Go
Flow with Friction and Heat Transfer
(1)
Created
Friction Coefficient
Go
Forces on sub-merged bodies
(9)
Verified
Circulation for lift force on a cylinder
Go
Verified
Freestream velocity for lift coefficient in a rotating cylinder with circulation
Go
Verified
Freestream velocity for lift coefficient with tangential speed
Go
Verified
Length of the cylinder for lift force on a cylinder
Go
Verified
Lift coefficient for a rotating cylinder with circulation
Go
Verified
Lift coefficient for a rotating cylinder with tangential speed
Go
Verified
Lift force on a cylinder for circulation
Go
Verified
Radius of cylinder for lift coefficient in a rotating cylinder with circulation
Go
Verified
Tangential velocity of the cylinder with the lift coefficient
Go
22 More Forces on sub-merged bodies Calculators
Go
Fundamentals of Inviscid Incompressible flow
(16)
Verified
Circulation by Kutta-Joukowski theorem
Go
Verified
Height difference of manometric fluid for given pressure difference
Go
Verified
Location of stagnation point outside the cylinder for lifting flow
Go
Verified
Pressure at a downstream point on streamline by Bernoulli's equation
Go
Verified
Pressure difference in the low-speed wind tunnel for given test section velocity
Go
Verified
Radial velocity for lifting flow over circular cylinder
Go
Verified
Radius of cylinder for non-lifting flow
Go
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
Verified
Stream function for non-lifting flow over a circular cylinder
Go
Verified
Surface pressure coefficient for lifting flow over circular cylinder
Go
Verified
Surface pressure on the body in terms of Pressure coefficient
Go
Verified
Velocity at a point on airfoil for given pressure coefficient and free-stream velocity
Go
Verified
Velocity potential for 2-D Vortex flow
Go
Verified
Velocity potential for uniform incompressible flow
Go
31 More Fundamentals of Inviscid Incompressible flow 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 a 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 for given glide angle
Go
Created
Lift-to-drag ratio for given glide angle
Go
Hypersonic Equivalence Principle and Blast-Wave Theory
(2)
Verified
Coefficient of drag equation using energy released from blast wave
Go
Verified
Modified Energy for the cylindrical blast wave
Go
14 More Hypersonic Equivalence Principle and Blast-Wave Theory Calculators
Go
Hypersonic Flow
(2)
Verified
Axial force coefficient
Go
Verified
Normal Force Coefficient
Go
18 More Hypersonic Flow Calculators
Go
Hypersonic Inviscid Flowfields: Approximate Methods
(1)
Verified
Transformed conical variable with cone angle in hypersonic flow
Go
11 More Hypersonic Inviscid Flowfields: Approximate Methods Calculators
Go
Hypersonic Small-Disturbance Equations
(1)
Verified
Similarity constant equation using the wave angle
Go
16 More Hypersonic Small-Disturbance Equations 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 the transition flow
Go
13 More Hypersonic Transition Calculators
Go
Hypersonic Viscous Interactions
(1)
Verified
Wall temperature over a flat plate under viscous, very high Mach flow
Go
17 More Hypersonic Viscous Interactions Calculators
Go
Ideal flow or Potential flow
(8)
Verified
Radial velocity at any radius
Go
Verified
Radius at any point considering radial velocity
Go
Verified
Stream function at a point
Go
Verified
Stream function at a point in the 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 a point in the combined flow
Go
7 More Ideal flow or Potential flow Calculators
Go
Incompressible flow over airfoil
(1)
Verified
Lift coefficient for symmetrical airfoil by Thin airfoil theory
Go
7 More Incompressible flow over airfoil Calculators
Go
Laminar boundary layer at a stagnation point on a 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 a stagnation point on a blunt body, Calculators
Go
Landing Performance
(5)
Created
Landing ground roll distance
Go
Created
Landing ground roll distance using thrust reversal
Go
Created
Stall velocity for given touchdown velocity
Go
Created
Touchdown velocity
Go
Created
Touchdown velocity for given stall velocity
Go
Lift-to-Drag
(3)
Created
Lift-to-drag ratio for given required thrust
Go
Created
Thrust required for given Lift-to-drag ratio
Go
Created
Weight of aircraft for given Lift-to-drag ratio
Go
Maneuvering Flight
(12)
Created
Load factor for a given pull-down maneuver radius
Go
Created
Load factor for a given pull-down maneuver rate
Go
Created
Load factor for a given pull-up maneuver radius
Go
Created
Load factor for a 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
Velocity for a given pull-down maneuver radius
Go
Created
Velocity for a given pull-down maneuver rate
Go
Created
Velocity for a given pull-up maneuver radius
Go
Created
Velocity for a given pull-up maneuver rate
Go
Merchant Force Circle (Mechanics of Orthogonal metal cutting)
(5)
Created
Shear angle for given area of shear plane, width of cut & uncut chip thickness
Go
Created
Shear force acting on shear plane for given shear stress & area of shear plane
Go
Created
Shear force on shear plane for given shear stress, width of cut, uncut chip thickness & shear angle
Go
Created
Uncut chip thickness for given width of cut, shear angle & area of shear plane
Go
Created
Width of cut for given shear angle, uncut chip thickness & area of shear plane
Go
33 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
Go
Metal Cutting and tools
(4)
Created
Back Rake Angle
Go
Created
Inclination Angle
Go
Created
Orthogonal Rake Angle
Go
Created
Side Rake Angle
Go
2 More Metal Cutting and tools Calculators
Go
Modern design-oriented code
(1)
Verified
Radiative heat transfer to the surface stemming from thermal radiation
Go
1 More Modern design-oriented code Calculators
Go
Normal Shock Waves
(17)
Created
Characteristic Mach number
Go
Created
Characteristic Mach Number behind shock
Go
Verified
Density ahead of normal shock using normal shock momentum equation
Go
Verified
Density behind normal shock using normal shock momentum equation
Go
Verified
Density ratio across a normal shock
Go
Created
Entropy change across normal shock
Go
Created
Mach Number behind the shock
Go
Created
Prandtl Condition
Go
Verified
Pressure ratio across a normal shock
Go
Created
Relation between Characteristic Mach number and Mach number
Go
Created
Shock strength
Go
Verified
Stagnation pressure behind normal shock by Rayleigh Pitot tube formula
Go
Verified
Static Pressure ahead of normal shock using normal shock momentum equation
Go
Verified
Static Pressure behind of normal shock using normal shock momentum equation
Go
Verified
Velocity ahead of normal shock from normal shock energy equation
Go
Created
Velocity behind a normal shock
Go
Verified
Velocity behind of normal shock from normal shock energy equation
Go
12 More Normal Shock Waves Calculators
Go
Notches and Weirs
(8)
Verified
Discharge over a broad-crested weir
Go
Verified
Discharge over rectangle notch or weir
Go
Verified
Discharge over rectangle weir for Bazin's formula with velocity approach
Go
Verified
Discharge over rectangle weir with two end contractions
Go
Verified
Head of liquid over the crest
Go
Verified
Length of section for discharge over rectangle notch or weir
Go
Verified
Length of weir considering Bazin's formula with velocity approach
Go
Verified
Length of weir for Discharge over a broad-crested weir
Go
19 More Notches and Weirs Calculators
Go
Oblique Shock and Expansion Waves
(8)
Created
Component of Downstream Mach normal to oblique shock
Go
Created
Component of Upstream Mach normal to oblique shock
Go
Created
Flow deflection angle
Go
Verified
Prandtl Meyer function
Go
Verified
Prandtl Meyer function at upstream Mach no.
Go
Verified
Pressure behind expansion fan
Go
Verified
Rearward Mach angle of the expansion fan
Go
Verified
Temperature behind expansion fan
Go
11 More Oblique Shock and Expansion Waves 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
Orifices and Mouthpieces
(9)
Verified
Co-efficient of discharge considering time of emptying a circular horizontal tank
Go
Verified
Co-efficient of velocity for the head of liquid and head loss
Go
Verified
Discharge through fully sub-merged orifice
Go
Verified
Discharge through large rectangular orifice
Go
Verified
Discharge through partially sub-merged orifice
Go
Verified
Head of liquid for head loss and coefficient of velocity
Go
Verified
Loss of head due to fluid resistance
Go
Verified
Theoretical velocity
Go
Verified
Time of emptying a circular horizontal tank
Go
24 More Orifices and Mouthpieces Calculators
Go
Plane walls
(10)
Verified
Area of the plane wall required for a given temperature difference
Go
Verified
Heat flow rate through a composite wall of 2 layers in series
Go
Verified
Heat flow rate through a composite wall of 3 layers in series
Go
Verified
Interface temperature of composite wall of 2 layers when inner surface temperature is known
Go
Verified
Length of the 2nd layer of the composite wall for a given temperature difference
Go
Verified
Outer surface temperature of a composite wall of 2 layers for a given heat flow rate
Go
Verified
Outer surface temperature of a composite wall of 3 layers for a given heat flow rate
Go
Verified
Outer surface temperature of the wall for a given heat flow rate
Go
Verified
Thermal conductivity of the material required to maintain a given temperature difference
Go
Verified
Thickness of the plane wall required for a given temperature difference
Go
12 More Plane walls Calculators
Go
Power Available and Maximum Velocity
(3)
Created
Power available for reciprocating engine-propeller combination
Go
Created
Propeller efficiency for reciprocating engine-propeller combination
Go
Created
Shaft brake power for reciprocating engine-propeller combination
Go
Power Required for Level Unaccelerated Flight
(10)
Created
Coefficient of Drag due to lift for minimum power required
Go
Created
Freestream velocity for given required power
Go
Created
Freestream Velocity for given total drag
Go
Created
Power required for given aerodynamic coefficients
Go
Created
Power required for given required thrust
Go
Created
Power required for given total drag
Go
Created
Thrust required for given required power
Go
Created
Total drag for given required power
Go
Created
Weight of aircraft for given required power
Go
Created
Zero-lift drag coefficient for minimum power required
Go
Range and Endurance of Jet Airplane
(7)
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
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
Range and Endurance of Propeller-Driven Airplane
(10)
Created
Endurance of Propeller-Driven Airplane
Go
Created
Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
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
Range of Propeller-Driven Airplane
Go
Created
Range of Propeller-Driven Airplane for given lift-to-drag ratio
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
Rate of Climb
(10)
Created
Excess power
Go
Created
Excess power for given rate of climb
Go
Created
Flight path angle at a given rate of climb
Go
Created
Rate of Climb
Go
Created
Rate of Climb for given excess power
Go
Created
Thrust available for given excess power
Go
Created
Total Drag for given excess power
Go
Created
Velocity of aircraft at a given rate of climb
Go
Created
Velocity of aircraft for given excess power
Go
Created
Weight of aircraft for given excess power
Go
Reference Temperature Method
(3)
Verified
Local turbulent skin-friction coefficient for incompressible flow
Go
Verified
Reynolds number for chord length using the Overall skin-friction drag coefficient
Go
Verified
Turbulent flat-plate skin-friction coefficient
Go
13 More Reference Temperature Method Calculators
Go
Relationship between Stick Force and Hinge Moment
(18)
Created
Control stick length for given gearing ratio
Go
Created
Elevator area for given stick force
Go
Created
Elevator chord length for given stick force
Go
Created
Elevator deflection angle for given gearing ratio
Go
Created
Elevator deflection angle for given stick force
Go
Created
Elevator Stick Force
Go
Created
Elevator Stick force for given gearing ratio
Go
Created
Elevator stick force for given hinge moment coefficient
Go
Created
Flight velocity for given stick force
Go
Created
Gearing ratio
Go
Created
Gearing ratio for given hinge moment coefficient
Go
Created
Gearing ratio for given stick force
Go
Created
Hinge moment coefficient for 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
Roll Stability
(5)
Created
Dihedral angle for given sideslip velocity
Go
Created
Forward velocity for given normal component of side velocity
Go
Created
Normal component of side velocity for given dihedral angle
Go
Created
Normal component of side velocity for given forward velocity
Go
Created
Sideslip velocity for given dihedral angle
Go
Tail Contribution
(21)
Created
Angle of attack at the tail
Go
Created
Angle of attack of the 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
Mean aerodynamic chord for given tail pitching moment coefficient
Go
Created
Pitching moment due to tail
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 of wing-tail combination
Go
Created
Tail lift for given tail pitching moment
Go
Created
Tail Pitching moment coefficient
Go
Created
Tail Pitching moment for given lift coefficient
Go
Created
Tail Pitching moment for given moment coefficient
Go
Created
Total Lift Coefficient of wing-tail combination
Go
Created
Total Lift of wing-tail combination
Go
Created
Vertical tail moment arm for given yawing moment coefficient
Go
Created
Wing Lift Coefficient of wing-tail combination
Go
Tail Contribution (Contd.)
(14)
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
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 pitching moment coefficient
Go
Created
Tail lift coefficient for given tail volume ratio
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 for given tail efficiency
Go
Created
Tail Pitching moment coefficient for given tail volume ratio
Go
Created
Wing Mean aerodynamic chord for given horizontal tail volume ratio
Go
Created
Wing Reference area for given horizontal tail volume ratio
Go
Takeoff Performance
(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
The Atmosphere
(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
The 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
Thrust Required for Level Unaccelerated Flight
(12)
Created
Coefficient of Lift for given thrust and weight
Go
Created
Coefficient of Lift for given thrust-to-weight ratio
Go
Created
Lift coefficient for given minimum required thrust
Go
Created
Lift for a level, unaccelerated flight at negligible thrust angle
Go
Created
Minimum Thrust required
Go
Created
Minimum Thrust required for given lift coefficient
Go
Created
Minimum Thrust required for given weight
Go
Created
Thrust for given coefficients of lift and drag
Go
Created
Thrust required for level, unaccelerated flight
Go
Created
Thrust-to-weight ratio
Go
Created
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Go
Created
Weight of aircraft for given coefficients of lift and drag
Go
Turbulent flow
(2)
Verified
Discharge through pipe for power required and head loss in turbulent flow
Go
Verified
Head loss due to friction for power required and discharge in turbulent flow
Go
5 More Turbulent flow Calculators
Go
Turning Flight
(12)
Created
Bank angle during level turn
Go
Created
Lift during level turn
Go
Created
Lift for a given load factor
Go
Created
Load factor
Go
Created
Load factor for a given turn radius
Go
Created
Load factor for a given turn rate
Go
Created
Turn radius
Go
Created
Turn rate
Go
Created
Velocity for a given turn radius
Go
Created
Velocity for a given turn rate
Go
Created
Weight during level turn
Go
Created
Weight for a given load factor
Go
Viscous flow
(6)
Verified
Buoyant force in falling sphere resistance method
Go
Verified
Density of fluid in falling sphere resistance method
Go
Verified
Diameter of sphere 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
Verified
Viscosity of fluid or oil in falling sphere resistance method
Go
46 More Viscous flow Calculators
Go
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