# Calculators Created by Vinay Mishra Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
339
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 339 and verified 141 calculators across 88 different categories till date.
Created Aerodynamic axial force
Created Aerodynamic normal force
Created Aerodynamic side force
Created Angle of attack
Created Normal force coefficient with aerodynamic normal force
Created Pitching moment
Created Pitching moment coefficient
Created Rolling moment
Created Rolling moment coefficient
Created Side force coefficient
Created Sideslip angle
Created Velocity along pitch axis for small sideslip angle
Created Velocity along roll axis for small angle of attack
Created Velocity along roll axis for small sideslip angle
Created Velocity along yaw axis for small angle of attack
Created Yawing moment
Created Yawing moment coefficient
Created Power required at an altitude
Created Power required at an altitude for given power required at sea-level condition
Created Power required at sea-level condition
Created Velocity at an altitude
Created Velocity at an altitude for given velocity at sea-level condition
Created Velocity at sea-level condition
Verified Adiabatic wall enthalpy over flat plate using Stanton number
Verified Freestream density over flat plate using Stanton number
Verified Freestream velocity over flat plate using Stanton number
Verified Wall enthalpy over flat plate using Stanton number
11 More Approximate Results Applied to Hypersonic Vehicles Calculators
Verified Critical Density
Verified Critical Pressure
Verified Critical Temperature
Created Ratio of Stagnation and Static Density
Created Ratio of stagnation and static pressure
Created Ratio of Stagnation and Static Temperature
Basics (2)
Verified Total thermal resistance for conduction through three resistances in series
Verified Total thermal resistance for conduction through two resistances in series
3 More Basics Calculators
Basics (7)
Verified Isentropic compressibility for given density and speed of sound
Created Mach Angle
Created Mach Number
Created Mayer's formula
Created Speed of Sound
Created Stagnation Temperature
Verified Thermal resistance for conduction through 2 resistances in parallel
Verified Pressure coefficient for blast wave theory at very high values of mach
Verified Pressure coefficient for Blunt-nosed plate:
4 More Blast-wave part 2 Calculators
Created Acceleration of system for given mass of body A
Created Acceleration of system for given mass of body B
Created Frictional force on body A
Created Frictional force on body B
Created Tension in string for given mass of body A
Created Tension in string for given mass of body B
Created Acceleration of system with bodies connected by string and lying on smooth inclined planes
Created Angle of inclination of plane with body A
Created Angle of inclination of plane with body B
Created Tension in string if both bodies are lying on smooth inclined planes
Created Acceleration of bodies
Created Mass of body B of smaller mass
Created Tension in the string if both the bodies are freely hanging
Created Acceleration of system with bodies one hanging free, other lying on rough inclined plane
Created Coefficient of friction for given frictional force
Created Coefficient of friction for given tension
Created Frictional force
Created Inclination of plane for given frictional force
Created Mass of body B for given frictional force
Created Tension in string given coefficient of friction of inclined plane
Created Acceleration of system with bodies one hanging free and other lying on rough horizontal plane
Created Tension in string given coefficient of friction of horizontal plane
Created Acceleration in system
Created Tension in string if only one body is freely suspended
Created Acceleration of system with bodies one hanging free and other lying on smooth inclined plane
Created Angle of inclination for given acceleration
Created Angle of inclination for given tension
Created Tension in string when one body is lying on smooth inclined plane
Verified Average coefficient of drag for drag force in boundary layer flows
Verified Drag force for average drag coefficient in boundary layer flows
Verified Freestream velocity for local drag coefficient in boundary layer flows
Verified Local drag coefficient for shear stress in boundary layer flows
Verified Shear stress for local drag coefficient in boundary layer flows
16 More Boundary layer flow Calculators
Verified Local skin-friction coefficient
Verified Stanton number with Reynolds number, Nusselt's number, Stanton number and Prandtl number
18 More Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions Calculators
Verified Centre of Buoyancy
Verified Meta-centric height for time period of oscillation and radius of gyration
Verified Radius of gyration for metacentric height and time period of oscillation
Verified Volume of fluid displaced
5 More Buoyancy Calculators
Verified Circulation for lift force on a cylinder
3 More Circulation Calculators
Verified Co-efficient of discharge considering time of emptying a circular horizontal tank
4 More Coefficient of Discharge Calculators
Verified Co-efficient of velocity for the head of liquid and head loss
2 More Coefficient of Velocity Calculators
Verified Lift coefficient for a rotating cylinder with circulation
Verified Lift coefficient for a rotating cylinder with tangential speed
4 More Coefficient's Calculators
Verified Bulk modulus for the velocity of sound wave
12 More Compressible flow Calculators
Created Moment produced by vertical tail for given lift curve slope
Created Moment produced by vertical tail for given side force
Created Sideslip angle for an Aircraft
Created Sideslip angle for given moment produced by vertical tail
Created Sidewash angle
Created Vertical tail angle of attack
Created Vertical tail angle of attack for given vertical tail side force
Created Vertical tail area for given vertical tail side force
Created Vertical tail dynamic pressure for given vertical tail side force
Created Vertical tail lift curve slope
Created Vertical tail lift curve slope for given moment
Created Vertical tail moment arm for given lift curve slope
Created Vertical tail moment arm for given side force
Created Vertical tail Side force
Created Vertical tail side force for given moment
Created Dynamic pressure at vertical tail for given yawing moment coefficient
Created Moment produced by vertical tail for given moment coefficient
Created Sideslip angle for given yawing moment coefficient
Created Sidewash angle for given moment produced by vertical tail
Created Sidewash angle for given yawing moment coefficient if wingspan is given
Created Vertical tail area for given moment
Created Vertical tail area for given yawing moment coefficient
Created Vertical tail dynamic pressure for given moment
Created Vertical tail lift curve slope for given yawing moment coefficient
Created Wing area for given moment produced by vertical tail
Created Wing dynamic pressure for given yawing moment coefficient
Created Wingspan for given yawing moment coefficient
Created Yawing moment coefficient for given vertical tail lift curve slope
Created Yawing moment coefficient when wingspan is given
Created Dynamic pressure at vertical tail for given vertical tail efficiency
Created Dynamic pressure at wing for given vertical tail efficiency
Created Dynamic pressure at wing for given yawing moment coefficient
Created Vertical tail area for given vertical tail volume ratio
Created Vertical tail efficiency
Created Vertical tail efficiency for given yawing moment coefficient
Created Vertical tail lift curve slope for given yawing moment coefficient and Vertical Tail Efficiency
Created Vertical tail moment arm for given vertical tail volume ratio
Created Vertical tail volume ratio
Created Vertical tail volume ratio for given yawing moment coefficient
Created Wing area for given vertical tail volume ratio
Created Wing area for given yawing moment coefficient
Created Wingspan for given vertical tail volume ratio
Created Wingspan for yawing moment coefficient given sideslip angle and sidewash angle
Created Yawing moment coefficient for given vertical tail volume ratio
Created Sideslip angle for yawing moment coefficient given vertical tail volume ratio
Created Sidewash angle for given yawing moment coefficient
Verified Heat flow rate through a cylindrical composite wall of 2 layers
Verified Heat flow rate through a cylindrical composite wall of 3 layers
Verified Heat flow rate through a cylindrical wall
Verified Inner surface temperature of a cylindrical wall for a given heat flow rate
Verified Outer surface temperature of a cylindrical wall for a given heat flow rate
Verified Outer surface temperature of the cylindrical composite wall of 2 layers
Verified Thermal conductivity of a cylindrical wall for a given temperature difference
Verified Thermal resistance for radial heat conduction offered by a cylinder wall
6 More Cylinders Calculators
Verified Discharge through fully sub-merged orifice
Verified Discharge through large rectangular orifice
Verified Discharge through partially sub-merged orifice
3 More Discharge Calculators
Verified Discharge over a broad-crested weir
Verified Discharge over rectangle notch or weir
Verified Discharge over rectangle weir for Bazin's formula with velocity approach
Verified Discharge over rectangle weir with two end contractions
9 More Discharge Calculators
Created Coefficient of Drag for given thrust and weight
Created Coefficient of Drag for given thrust-to-weight ratio
Created Drag for a level, unaccelerated flight at negligible thrust angle
Created Lift-induced drag coefficient for given required thrust
Created Zero-lift drag coefficient at minimum required thrust
Created Zero-lift drag coefficient for given lift coefficient
Created Zero-lift drag coefficient for given required thrust
Created Elevator area for given hinge moment coefficient
Created Elevator chord length for given hinge moment coefficient
Created Elevator Hinge moment coefficient
Created Elevator Hinge moment for given hinge moment coefficient
Created Flight velocity for given elevator hinge moment coefficient
Created Centrifugal Force in an accelerated flight
Created Drag for a level, unaccelerated flight
Created Drag in an accelerated flight
Created Lift for an unaccelerated flight
Created Lift in an accelerated flight
Created Thrust angle for an unaccelerated flight for given drag
Created Thrust angle for an unaccelerated flight for given lift
Created Thrust for a level, unaccelerated flight
Created Thrust in an accelerated flight
Created Velocity in an accelerated flight
Created Weight of aircraft in level, unaccelerated flight
Verified Recovery factor calculation using Prandtl number
Verified Recovery factor for flat plate with viscous flow
Verified Skin-friction drag Coefficient
12 More Flat-Plate for Viscous flow case Calculators
Created Lift Coefficient for given turn radius
Created Lift Coefficient for given turn rate
Created Load factor for given turn radius for a high-performance fighter aircraft
Created Load factor for given turn rate for a high-performance fighter aircraft
Created Radius of turn for given lift coefficient
Created Turn rate for given lift coefficient
Created Turn rate for high load factor
Created Velocity for given turn rate for a high load factor
Verified Intensity of pressure wave produced for gradual closure of valves
Verified Time required to close the valve for gradual closure of valves
14 More Flow through pipes Calculators
Created Friction Coefficient
Verified Length of the cylinder for lift force on a cylinder
Verified Lift force on a cylinder for circulation
Verified Radius of cylinder for lift coefficient in a rotating cylinder with circulation
12 More Forces on sub-merged bodies Calculators
Verified Circulation by Kutta-Joukowski theorem
Verified Height difference of manometric fluid for given pressure difference
Verified Location of stagnation point outside cylinder for lifting flow
Verified Radius of cylinder for non-lifting flow
Verified Source Strength for 2-D incompressible source flow
Verified Stagnation streamline equation for flow over semi-infinite body
Verified Velocity at a point on airfoil for given pressure coefficient and free-stream velocity
8 More Fundamentals of Inviscid Incompressible flow Calculators
Created Degree of freedom
Created Number of Components
Created Number of Phases
Created Total Number of Variables in System
Created Drag for given glide angle
Created Glide angle
Created Glide angle for given lift-to-drag ratio
Created Lift for given glide angle
Created Lift-to-drag ratio for given glide angle
Verified Coefficient of drag equation using energy released from blast wave
Verified Modified Energy for the cylindrical blast wave
14 More Hypersonic Equivalence Principle and Blast-Wave Theory Calculators
Verified Axial force coefficient
Verified Normal Force Coefficient
18 More Hypersonic Flow Calculators
Verified Reynolds number equation using boundary-layer momentum thickness
Verified Reynolds number equation using local Mach number
Verified Thermal conductivity of the transition flow
13 More Hypersonic Transition Calculators
Verified Wall temperature over a flat plate under viscous, very high Mach flow
17 More Hypersonic Viscous Interactions Calculators
Verified Stream function at a point
Verified Stream function at a point in the combined flow
Verified Stream function in sink flow for angle
Verified Strength of doublet for stream function
Verified Uniform flow velocity for stream function at a point in the combined flow
7 More Ideal flow or Potential flow Calculators
Verified Lift coefficient for symmetrical airfoil by Thin airfoil theory
7 More Incompressible flow over airfoil Calculators
Verified Reynolds analogy factor in Finite deference method
Verified Reynolds analogy for Stanton number in finite difference method
5 More Laminar boundary layer at a stagnation point on a blunt body, Calculators
Created Landing ground roll distance
Created Landing ground roll distance using thrust reversal
Created Stall velocity for given touchdown velocity
Created Touchdown velocity
Created Touchdown velocity for given stall velocity
Verified Length of weir considering Bazin's formula with velocity approach
Verified Length of weir for Discharge over a broad-crested weir
6 More Length of Weir Calculators
Created Lift-to-drag ratio for given required thrust
Created Thrust required for given Lift-to-drag ratio
Created Weight of aircraft for given Lift-to-drag ratio
Verified Loss of head due to sudden enlargement at any particular section of pipe
6 More Loss of Head Calculators
Created Load factor for a given pull-down maneuver rate
Created Load factor for a given pull-up maneuver rate
Created Pull-down maneuver rate
Created Pull-up maneuver rate
Created Velocity for a given pull-down maneuver radius
Created Velocity for a given pull-down maneuver rate
Created Velocity for a given pull-up maneuver radius
Created Velocity for a given pull-up maneuver rate
Created Shear angle for given area of shear plane, width of cut & uncut chip thickness
Created Shear force acting on shear plane for given shear stress & area of shear plane
Created Shear force on shear plane for given shear stress, width of cut, uncut chip thickness & shear angle
Created Uncut chip thickness for given width of cut, shear angle & area of shear plane
Created Width of cut for given shear angle, uncut chip thickness & area of shear plane
17 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
Created Back Rake Angle
Created Inclination Angle
Created Orthogonal Rake Angle
Created Side Rake Angle
2 More Metal Cutting and tools Calculators
1 More Modern design-oriented code Calculators
Created Characteristic Mach number
Created Characteristic Mach Number behind shock
Verified Density ahead of normal shock using normal shock momentum equation
Verified Density behind normal shock using normal shock momentum equation
Verified Density ratio across a normal shock
Created Entropy change across normal shock
Created Mach Number behind the shock
Created Prandtl Condition
Verified Pressure ratio across a normal shock
Created Relation between Characteristic Mach number and Mach number
Created Shock strength
Verified Stagnation pressure behind normal shock by Rayleigh Pitot tube formula
Verified Static Pressure ahead of normal shock using normal shock momentum equation
Verified Static Pressure behind of normal shock using normal shock momentum equation
Verified Velocity ahead of normal shock from normal shock energy equation
Created Velocity behind a normal shock
Verified Velocity behind of normal shock from normal shock energy equation
12 More Normal Shock Waves Calculators
Verified Head of liquid over the crest
Verified Length of section for discharge over rectangle notch or weir
4 More Notches and Weirs Calculators
Created Component of Downstream Mach normal to oblique shock
Created Component of Upstream Mach normal to oblique shock
Created Flow deflection angle
Verified Prandtl Meyer function
Verified Prandtl Meyer function at upstream Mach number
Verified Pressure behind expansion fan
Verified Rearward Mach angle of the expansion fan
Verified Temperature behind expansion fan
11 More Oblique Shock and Expansion Waves Calculators
Created Dynamic pressure for given specific heat ratio and Mach number
Verified Velocity of sound using dynamic pressure and density
13 More oblique shock relation Calculators
Verified Loss of head due to fluid resistance
Verified Theoretical velocity
13 More Orifices and Mouthpieces Calculators
Verified Area of the plane wall required for a given temperature difference
Verified Heat flow rate through a composite wall of 2 layers in series
Verified Heat flow rate through a composite wall of 3 layers in series
Verified Interface temperature of composite wall of 2 layers given inner surface temperature
Verified Length of 2nd layer of composite wall for a given temperature difference
Verified Outer surface temperature of a composite wall of 2 layers for a given heat flow rate
Verified Outer surface temperature of a composite wall of 3 layers for a given heat flow rate
Verified Outer surface temperature of the wall for a given heat flow rate
Verified Thermal conductivity of the material required to maintain a given temperature difference
Verified Thickness of the plane wall required for a given temperature difference
12 More Plane walls Calculators
Created Power available for reciprocating engine-propeller combination
Created Propeller efficiency for reciprocating engine-propeller combination
Created Shaft brake power for reciprocating engine-propeller combination
Created Coefficient of Drag due to lift for minimum power required
Created Freestream velocity for given required power
Created Freestream Velocity for given total drag
Created Power required for given aerodynamic coefficients
Created Power required for given required thrust
Created Power required for given total drag
Created Thrust required for given required power
Created Total drag for given required power
Created Weight of aircraft for given required power
Created Zero-lift drag coefficient for minimum power required
Verified Pressure at a downstream point on streamline by Bernoulli's equation
Verified Pressure difference in low-speed wind tunnel for given test section velocity
Verified Surface pressure coefficient for lifting flow over circular cylinder
Verified Surface pressure on body in terms of Pressure coefficient
8 More Pressure Calculators
Verified Radial velocity for lifting flow over circular cylinder
Created Endurance for given Lift-to-Drag ratio of Jet Airplane
Created Endurance of Jet Airplane
Created Lift-to-Drag ratio for given Endurance of Jet Airplane
Created Range of Jet Airplane
Created Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
Created Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane
Created Thrust-Specific Fuel Consumption for given Range of Jet Airplane
Created Endurance of Propeller-Driven Airplane
Created Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
Created Propeller Efficiency for given Endurance of Propeller-Driven Airplane
Created Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Created Propeller Efficiency for given Range of Propeller-Driven Airplane
Created Range of Propeller-Driven Airplane
Created Range of Propeller-Driven Airplane for given lift-to-drag ratio
Created Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
Created Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Created Specific Fuel Consumption for given Range of Propeller-Driven Airplane
Created Excess power
Created Excess power for given rate of climb
Created Flight path angle at given rate of climb
Created Rate of Climb
Created Rate of Climb for given excess power
Created Thrust available for given excess power
Created Total Drag for given excess power
Created Velocity of aircraft at a given rate of climb
Created Velocity of aircraft for given excess power
Created Weight of aircraft for given excess power
Verified Local turbulent skin-friction coefficient for incompressible flow
Verified Reynolds number for chord length using the Overall skin-friction drag coefficient
Verified Turbulent flat-plate skin-friction coefficient
12 More Reference Temperature Method Calculators
Created Control stick length for given gearing ratio
Created Elevator area for given stick force
Created Elevator chord length for given stick force
Created Elevator deflection angle for given gearing ratio
Created Elevator deflection angle for given stick force
Created Elevator Stick Force
Created Elevator Stick force for given gearing ratio
Created Elevator stick force for given hinge moment coefficient
Created Flight velocity for given stick force
Created Gearing ratio
Created Gearing ratio for given hinge moment coefficient
Created Gearing ratio for given stick force
Created Hinge moment coefficient for given stick force
Created Hinge moment for given gearing ratio
Created Hinge moment for given stick force
Created Stick deflection angle for given gearing ratio
Created Stick deflection angle for given stick force
Created Stick length for given stick force
Created Dihedral angle for given sideslip velocity
Created Forward velocity for given normal component of side velocity
Created Normal component of side velocity for given dihedral angle
Created Normal component of side velocity for given forward velocity
Created Sideslip velocity for given dihedral angle
Verified Stream function for 2-D incompressible source flow
Verified Stream function for non-lifting flow over a circular cylinder
7 More Stream Function Calculators
Created Angle of attack at the tail
Created Angle of attack of the wing
Created Angle of incidence of tail
Created Angle of incidence of wing
Created Downwash angle
Created Lift due to tail only
Created Lift due to wing only
Created Mean aerodynamic chord for given tail pitching moment coefficient
Created Pitching moment due to tail
Created Tail area for given tail efficiency
Created Tail Efficiency for given lift coefficients
Created Tail lift coefficient for given pitching moment
Created Tail Lift Coefficient of wing-tail combination
Created Tail lift for given tail pitching moment
Created Tail Pitching moment coefficient
Created Tail Pitching moment for given lift coefficient
Created Tail Pitching moment for given moment coefficient
Created Total Lift Coefficient of wing-tail combination
Created Total Lift of wing-tail combination
Created Vertical tail moment arm for given yawing moment coefficient
Created Wing Lift Coefficient of wing-tail combination
Created Horizontal tail area for given tail volume ratio
Created Horizontal tail volume ratio
Created Horizontal tail volume ratio for given pitching moment coefficient
Created Tail area for given tail moment coefficient
Created Tail Efficiency for given pitching moment coefficient
Created Tail Efficiency for given tail volume ratio
Created Tail lift coefficient for given pitching moment coefficient
Created Tail lift coefficient for given tail volume ratio
Created Tail moment arm for given horizontal tail volume ratio
Created Tail moment arm for given tail moment coefficient
Created Tail Pitching moment coefficient for given tail efficiency
Created Tail Pitching moment coefficient for given tail volume ratio
Created Wing Mean aerodynamic chord for given horizontal tail volume ratio
Created Wing Reference area for given horizontal tail volume ratio
Created Coefficient of rolling friction during ground roll
Created Drag during ground effect
Created Ground effect factor
Created Lift acting on aircraft during ground roll
Created Liftoff distance
Created Liftoff velocity for given stall velocity
Created Liftoff velocity for given weight
Created Maximum Lift coefficient for given liftoff velocity
Created Maximum Lift coefficient for given stall velocity
Created Resistance force during ground roll
Created Stall velocity for given liftoff velocity
Created Stall velocity for given weight
Created Thrust for given liftoff distance
Created Weight of aircraft during ground roll
Created Absolute altitude
Created Geometric altitude
Created Geometric altitude for given geopotential altitude
Created Geopotential altitude
Created Lapse rate
Created Coefficient of Drag due to lift
Created Drag Coefficient for given parasite drag coefficient
Created Drag Coefficient for given zero-lift drag coefficient
Created Parasite Drag Coefficient at zero lift
Created Coefficient of Lift for given thrust and weight
Created Coefficient of Lift for given thrust-to-weight ratio
Created Lift coefficient for given minimum required thrust
Created Lift for a level, unaccelerated flight at negligible thrust angle
Created Minimum Thrust required
Created Minimum Thrust required for given lift coefficient
Created Minimum Thrust required for given weight
Created Thrust for given coefficients of lift and drag
Created Thrust required for level, unaccelerated flight
Created Thrust-to-weight ratio
Created Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Created Weight of aircraft for given coefficients of lift and drag
Verified Time of emptying a circular horizontal tank
2 More Time of Emptying Calculators
Verified Discharge through pipe for power required and head loss in turbulent flow
Verified Head loss due to friction for power required and discharge in turbulent flow
5 More Turbulent flow Calculators
Created Bank angle during level turn
Created Lift during level turn
Created Lift for a given load factor
Created Load factor for a given turn rate
Created Load factor given Lift Force and Weight
Created Turn rate
Created Velocity for a given turn radius
Created Velocity for a given turn rate
Created Weight during level turn
Created Weight for a given load factor
Verified Freestream velocity for lift coefficient in a rotating cylinder with circulation
Verified Freestream velocity for lift coefficient with tangential speed
Verified Tangential velocity of the cylinder with the lift coefficient
3 More Velocity Calculators
Verified Velocity of sphere in falling sphere resistance method
4 More Velocity Calculators
Verified Velocity at section 1-1 for sudden enlargement
Verified Velocity at section 2-2 for sudden enlargement
7 More Velocity of Flow Calculators
Verified Velocity of sound wave in terms of bulk modulus
4 More Velocity of Sound Wave Calculators
Verified Velocity potential for 2-D Vortex flow
Verified Velocity potential for uniform incompressible flow
3 More Velocity Potential Calculators
Verified Viscosity of fluid or oil in falling sphere resistance method
3 More Viscosity of Fluid Calculators
Verified Buoyant force in falling sphere resistance method
Verified Density of fluid in falling sphere resistance method
Verified Diameter of sphere in falling sphere resistance method
Verified Drag force in falling sphere resistance method
16 More Viscous flow Calculators Let Others Know