# Calculators Created by Sanjay Krishna Amrita School of Engineering (ASE), Vallikavu
299
Formulas Created
200
Formulas Verified
106
Across Categories

## List of Calculators by Sanjay Krishna

Following is a combined list of all the calculators that have been created and verified by Sanjay Krishna. Sanjay Krishna has created 299 and verified 200 calculators across 106 different categories till date.
Verified Velocity along roll axis for small sideslip angle
Verified Velocity along yaw axis for small angle of attack
Verified Yawing moment
Verified Yawing moment coefficient
13 More Aerodynamic Nomenclature Calculators
Verified Velocity at Altitude
6 More Altitude Effects on Power Required and Available Calculators
Created Adiabatic wall enthalpy over flat plate using Stanton number
Created Coefficient of drag over flat under freestream flow conditions
Created Drag force over flat plate
Created Free stream enthalpy over flat plate with freestream conditions
Created Free stream velocity over flat plate using drag force
Created Free stream velocity over flat plate with freestream conditions
Created Freestream density over flat plate using Stanton number
Created Freestream density over flat under freestream flow conditions
Created Freestream Stanton number for flat plate
Created Freestream velocity over flat plate using Stanton number
Created Local heat transfer over flat plate using Stanton number
Created Pressure ratio for insulated flat plate, the strong interaction
Created Pressure ratio for insulated flat plate, the weak interaction
Created Total enthalpy over flat plate with freestream conditions
Created Wall enthalpy over flat plate using Stanton number
Verified Ratio of Stagnation and Static Density
Verified Ratio of Stagnation and Static Temperature
4 More Basic Compressible Flow Calculators
Basics (2)
Verified Mach Angle
Verified Mayer's formula
6 More Basics Calculators
Basics (2)
Verified Thermal conductance for given thermal resistance
Verified Total thermal resistance for conduction through two resistances in parallel
3 More Basics Calculators
Created Pressure coefficient combined with blast wave for shuttle
Created Pressure coefficient combined with blast wave for shuttle at angle of attack
Created Pressure coefficient for blast wave theory
Created Pressure coefficient for blast wave theory at very high values of mach
Created Pressure coefficient for Blunt-nosed cylinder:
Created Pressure coefficient for Blunt-nosed plate:
Verified Frictional force on body A
5 More Bodies connected by string and lying on rough inclined planes Calculators
Verified Acceleration of system with bodies connected by string and lying on smooth inclined planes
Verified Tension in string if both bodies are lying on smooth inclined planes
2 More Bodies connected by string and lying on smooth inclined planes Calculators
Verified Acceleration of system with bodies one hanging free, other lying on rough inclined plane
Verified Coefficient of friction for given tension
Verified Inclination of plane for given frictional force
Verified Mass of body B for given frictional force
Verified Tension in string given coefficient of friction of inclined plane
2 More Bodies connected by string, one hanging free, other lying on a rough inclined plane Calculators
Verified Tension in string given coefficient of friction of horizontal plane
1 More Bodies connected by string, one hanging free, other lying on rough horizontal plane Calculators
Verified Acceleration of system with bodies one hanging free and other lying on smooth inclined plane
Verified Angle of inclination for given acceleration
Verified Angle of inclination for given tension
1 More Bodies connected by string, one hanging free, other lying on smooth inclined plane Calculators
Created Lattice Constant of BCC
Created Total volume of atoms in BCC
Verified Area of surface for average drag coefficient in boundary layer flows
Verified Distance from leading edge for Blasius's solution in boundary layer flow
Verified Distance from leading edge in boundary layer flow
Verified Length of the plate for Reynold number in the laminar boundary layer flow
Verified Reynold number at the end of the plate
Verified Reynold number for drag coefficient in Blasius's solution of boundary layer flow
Verified Shear stress at the boundary for turbulent boundary layer over a flat plate
Verified Thickness of boundary layer for Blasius's solution in boundary layer flow
Verified Thickness of boundary layer in boundary layer flow
Verified Velocity of fluid for Reynold number in the laminar boundary layer flow
11 More Boundary layer flow Calculators
Created Adiabatic wall enthalpy using Stanton number
Created Dynamic viscosity around wall
Created Enthalpy of wall using Stanton number
Created Local heat transfer rate using Nusselt's number
Created Local heat-transfer rate calculation using Stanton number
Created Local shear stress at wall
Created Local skin-friction coefficient
Created Nusselt number for hypersonic vehicle
Created Nusselt's number with Reynolds number, Stanton number and Prandtl number
Created Prandtl number with Reynolds number, Nusselt's number, and Stanton number
Created Reynolds number for given Nusselt's number, Stanton number and Prandtl number
Created Skin friction coefficient for incompressible flow
Created Stanton number for hypersonic vehicle
Created Stanton number with Reynolds number, Nusselt's number, Stanton number and Prandtl number
Created Static Density equation using skin friction coefficient
Created Static density equation using Stanton number
Created Static velocity equation using skin friction coefficient
Created Static velocity using Stanton number
Created Static viscosity relation using temperature of wall
Created Thermal conductivity at edge of boundary layer equation using Nusselt's number
Verified Angle of heel for metacentric height in experimental method
Verified Meta-centric height in experimental method
Verified Movable weight for metacentric height in experimental method
6 More Buoyancy Calculators
Verified Circulation for a single stagnation point
4 More Circulation Calculators
Verified Coefficient of Discharge given Time of Emptying Hemispherical Tank
4 More Coefficient of Discharge Calculators
Verified Coefficient of velocity
2 More Coefficient of Velocity Calculators
Verified Coefficient of drag for sphere in Oseen formula when Reynolds number is between 0.2 and 5
Verified Coefficient of drag for sphere in stoke's law when Reynolds number is less than 0.2
4 More Coefficient's Calculators
Verified Absolute temperature for the velocity of sound wave in the isothermal process
Verified Absolute temperature for velocity of sound wave in terms of adiabatic process
Verified Density of fluid considering velocity at outlet of orifice
Verified Pressure ratio for maximum flow rate through nozzle or orifice
Verified Temperature of fluid for stagnation temperature considering compressible fluid flow
8 More Compressible flow Calculators
Created Emissivity
Created Freestream density
Created Freestream velocity
Created Reference viscosity
Verified Sidewash angle
14 More Contribution of Aircraft Components- Part 1 Calculators
Verified Dynamic pressure at vertical tail for given vertical tail efficiency
Verified Dynamic pressure at wing for given vertical tail efficiency
Verified Vertical tail efficiency
12 More Contribution of Aircraft Components- Part 3 Calculators
Created Atomic Packing Factor
Created Cutting Force given Thrust Force and Normal Rake Angle
5 More Cutting Force Calculators
Verified Total thermal resistance of 2 cylindrical resistances connected in series.
Verified Total thermal resistance of 3 cylindrical resistances connected in series
Verified Total Thermal Resistance of Cylindrical wall with Convection on both Sides
11 More Cylinders Calculators
Verified Diameter of pipe for difference in pressure in viscous flow
Verified Diameter of pipe for head loss due to friction in viscous flow
Verified Diameter of pipe for loss of pressure head in viscous flow
Verified Discharge in Borda's Mouthpiece Running Free
Verified Discharge in Borda's Mouthpiece Running Full
Verified Discharge in Convergent-Divergent Mouthpiece
3 More Discharge Calculators
Verified Coefficient of Discharge for Time required to Empty Reservoir
12 More Discharge Calculators
Verified Coefficient of Drag for given thrust and weight
Verified Lift-induced drag coefficient for given required thrust
5 More Drag during Level Unaccelerated Flight Calculators
Verified Drag force for a body moving in a fluid of certain density
Verified Total drag force on a sphere
5 More Drag Force on Body Calculators
Verified Actual discharge in venturimeter
Verified Difference in pressure head for heavier liquid in manometer
Verified Difference in pressure head for light liquid in manometer
Verified Velocity at any point for coefficient of pitot-tube
2 More Dynamics of fluid flow Calculators
Created Emissivity per unit mole
Created Kinetic energy per mole
Created Kinetic energy per mole using molar volume
Created Kinetic energy per mole using temperature of gas
Created Mean free path of single-species gas
Created Mean free path using number density
Created Molar volume using kinetic energy per mole
Created Number density
Created Pressure of gas using number density
Created Pressure using kinetic energy per mole
Created Pressure using molar volume
Created Specific gas constant using kinetic energy per mole
Created Temperature of gas using Emissivity per unit mole
Created Temperature of gas using kinetic energy per mole
Created Volume of gas
Verified Elevator deflection angle for given gearing ratio
3 More Elevator and Stick Deflection Angles Calculators
Verified Enthalpy ahead of normal shock from normal shock energy equation
Verified Enthalpy behind of normal shock from normal shock energy equation
Verified Velocity ahead of normal shock by normal shock momentum equation
Verified Velocity behind of normal shock by normal shock momentum equation
Verified Velocity upstream of shock using Prandtl relation
6 More Enthalpy and Velocity Calculators
Created Lattice Constant of FCC
Created Volume of atoms in FCC
Created Adiabatic wall enthalpy for flat plate
Created Adiabatic wall enthalpy using recovery factor
Created Aerodynamic Heating Equation for Stanton number
Created Coefficient of friction using Stanton number for flat plat case
Created Drag per unit span
Created Prandtl number for flat plate with viscous flow
Created Recovery factor calculation using Prandtl number
Created Recovery factor for flat plate with viscous flow
Created Recovery Factor using temperature
Created Skin-friction drag Coefficient
Created Skin-friction drag for flat plate in viscous flow
Created Stanton number with coefficient of friction
Created Static density equation using aerodynamic equation
Created Static velocity equation using aerodynamic heating equation
Created Total enthalpy in inviscid flow outside boundary layer
14 More Flight Envelope Calculators
Verified Bazin's constant
Verified Chezy's constant considering Bazin formula
Verified Chezy's constant considering velocity
Verified Critical depth considering flow in open channels
Verified Critical depth considering minimum specific energy
Verified Critical depth considering the critical velocity
Verified Critical velocity considering flow in open channels
Verified Discharge per unit width considering flow in open channels
Verified Hydraulic mean depth considering Bazin formula
Verified Hydraulic mean depth using Chezy's formula
Verified Minimum specific energy considering the critical depth
Verified Velocity of Chezy's formula
7 More Flow in open channels Calculators
Verified Coefficient of contraction for sudden contraction
Verified Difference in liquid level in three compound pipes with same friction coefficient
Verified Maximum area of obstruction in the pipe
Verified Power lost due to sudden enlargement
Verified Power transmission through pipes
Verified Retarding force for gradual closure of valves
Verified Time taken by pressure wave to travel
14 More Flow through pipes Calculators
Verified Airspeed measurement by Pitot tube for low-speed incompressible flow
Verified Lift per unit span by Kutta-Joukowski theorem
13 More Fundamentals of Inviscid Incompressible flow Calculators
Verified Control stick length for given gearing ratio
3 More Gearing Ratio Calculators
Verified Lift force for given glide angle
Verified Lift-to-drag ratio for given glide angle
3 More Gliding Flight Calculators
Verified Head available at the base of the nozzle
Verified Total head at the inlet of pipe for head available at the base of the nozzle
Verified Total head available at inlet of pipe for efficiency of power transmission
Verified Hinge moment coefficient for given stick force
2 More Hinge Moment Calculators
Created Blunt-nosed flat plate pressure ratio (first approximation)
Created Boltzmann constant for cylindrical blast wave
Created Coefficient of drag equation using energy released from blast wave
Created Creation pressure for planar blast wave
Created Energy for blast wave
Created Modified Energy for cylindrical blast wave
Created Modified pressure equation for cylindrical blast wave
Created Modified Radial coordinate equation for cylindrical blast wave
Created Pressure for cylindrical blast wave
Created Pressure ratio for blunt cylinder blast wave
Created Pressure ratio for blunt slab blast wave
Created Radial coordinate for planar blast wave
Created Radial coordinate of blunt slab blast wave
Created Radial coordinate of cylindrical blast wave
Created Simplified pressure ratio for blunt cylinder blast wave
Created Time required for blast wave
Created Blunt-nosed radial coordinate flat plate (first approximation):
Created Forces acting on body along flight path
Created Forces acting Perpendicular to body on flight path
Created Pressure ratio of Blunt-nosed cylinder (first approximation):
Created Radial coordinate of Blunt-nosed cylinder (first approximation):
Created Radius for cylinder-wedge body shape
Created Radius for sphere-cone body shape
Created Radius of curvature for cylinder wedge body shape
Created Radius of curvature for sphere cone body shape
Created Axial force coefficient
Created Coefficient of drag
Created Coefficient of pressure with similarity parameters
Created Deflection angle
Created Drag force
Created Dynamic pressure
Created Dynamic Pressure given Coefficient of Lift
Created Fourier's Law of Heat Conduction
Created Hypersonic similarity parameter
Created Lift coefficient
Created Lift Force
Created Mach number with fluids
Created Mach ratio at high mach number
Created Moment coefficient
Created Newtonian sine squared law for pressure coefficient
Created Normal Force Coefficient
Created Pressure ratio for high Mach number
Created Pressure ratio having high mach number with similarity constant
Created Shear-stress distribution.
Created Supersonic expression for pressure coefficient on surface with local deflection angle
Created Non dimensional radius for hypersonic vehicles
Created Non-dimensional density
Created Non-dimensional density for high mach number
Created Non-dimensional parallel velocity component for high mach number
Created Non-dimensional perpendicular velocity component for high mach number
Created Non-dimensional pressure
Created Non-dimensional pressure for high mach number
Created Slenderness ratio with cone radius for hypersonic vehicle
Created Transformed conical variable
Created Transformed conical variable with cone angle in hypersonic flow
Created Transformed conical variable with wave angle
Created Density before shock formation for compression wave
Created Density before the shock formation for expansion wave
Created Detachment distance of cylinder wedge body shape
Created Detachment distance of sphere cone body shape
Created Grid point calculation for shock waves
Created Local shock velocity equation
Created Mach wave behind shock
Created Mach wave behind shock with mach infinity
Created New pressure after shock formation for compression wave
Created New pressure after shock formation, subtracted to velocity for expansion wave
Created Nose radius of sphere cone
Created Pressure ratio for unsteady waves
Created Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves
Created Ratio of new and old temperature
Created Ratio of new and old temperature for expansion waves
Created Temperature ratio for unsteady compression waves
Created Temperature ratio for unsteady expansion wave
Created Change in velocity for hypersonic flow in x direction
Created Coefficient of pressure with slenderness ratio
Created Coefficient of pressure with slenderness ratio and similarity constant
Created Constant g used for finding the location of perturbed shock
Created Density ratio with similarity constant having slenderness ratio
Created Distance from tip of leading edge to base
Created Doty and Rasmussen - normal-force coefficient
Created Inverse of density for hypersonic flow
Created Inverse of density for hypersonic flow using Mach number
Created Non dimensional Change in hypersonic disturbance velocity in x direction
Created Non dimensional Change in hypersonic disturbance velocity in y direction
Created Non dimensional pressure equation with slenderness ratio
Created Non dimensional Velocity disturbance in y direction in hypersonic flow
Created Non- dimensionalised time
Created Rasmussen closed form expression for shock wave angle
Created Similarity constant equation using wave angle
Created Similarity constant equation with slenderness ratio
Created Boundary-layer momentum thickness using Reynolds number at transition point
Created Eddy viscosity calculation
Created Local Mach Number using Reynolds number equation at transition region
Created Location of transition point
Created Prandtl number of transition flow
Created Reynolds number equation using boundary-layer momentum thickness
Created Reynolds number equation using local Mach number
Created Specific heat at constant pressure for transient flow
Created Static density at transition point
Created Static density equation using boundary-layer momentum thickness
Created Static velocity at transition point
Created Static velocity using boundary-layer momentum thickness
Created Static viscosity at transition point
Created Static viscosity equation using boundary-layer momentum thickness
Created Thermal conductivity of transition flow
Created Transition Reynolds number
Created Large Mach number over flat plate using static temperature and wall temperature
Created Mach number over flat plate using static temperature and wall temperature
Created Pressure ratio for cold-wall case the strong interaction
Created Pressure ratio for cold-wall case the weak interaction
Created Static density of fluid over flat plate
Created Static temperature of fluid over flat plate
Created Static temperature of plate using wall viscosity
Created Static temperature over flat plate under viscous, very high Mach flow
Created Static temperature over flat plate using Static Mach Number
Created Static viscosity using wall temperature and static temperature
Created Total temperature over flat plate under viscous Mach flow
Created Total temperature over flat plate under viscous very high Mach flow
Created viscosity of wall using wall temperature and static temperature
Created Wall density of fluid over flat plate
Created Wall temperature of fluid over the flat plate
Created Wall temperature of plate using wall viscosity
Created Wall temperature over flat plate under viscous, very high Mach flow
Created Wall temperature over flat plate using Static Mach Number
14 More Ideal flow or Potential flow Calculators
Verified Boundary layer thickness for Turbulent flow
Verified Center of pressure location for cambered airfoil
Verified Skin friction drag coefficient for flat plate in laminar flow
Verified Skin friction drag coefficient for flat plate in Turbulent flow
4 More Incompressible flow over airfoil Calculators
Verified Height or depth of paraboloid for volume of air
Verified Total Pressure Force at Bottom of Cylinder
Verified Total pressure force on top of cylinder
4 More Kinematics of flow Calculators
Created Newtonian Dynamic pressure
Created Newtonian pressure distribution over the surface using cosine angle
Created Nusselt number at stagnation point
Created Nusselt number for stagnation point on blunt body
Created Reynolds analogy factor in Finite deference method
Created Reynolds analogy for Stanton number in finite difference method
Created Stagnation pressure
Verified Landing ground roll distance
3 More Landing Performance Calculators
Verified Length of pipe for difference of pressure in viscous flow
Verified Length of pipe for head loss due to friction in viscous flow
Verified Length of pipe for loss of pressure head in viscous flow
Verified Flight velocity for given elevator hinge moment coefficient
4 More Longitudinal Control of Elevator Hinge Moment Calculators
Verified Loss of head due to friction
Verified Loss of pressure head for viscous flow through circular pipe
1 More Loss of Head Calculators
Verified Head loss due to friction for the efficiency of power transmission
Verified Loss of head at the exit of pipe
Verified Loss of head due to obstruction in pipe
5 More Loss of Head Calculators
Created Area of shear plane for given shear angle, width of cut & uncut chip thickness
Created Coefficient of friction for given friction angle
Created Coefficient of friction for given thrust force, cutting force and normal rake angle
Created Coefficient of Friction given Forces Normal and along Tool Rake Face
Created Force acting Normal to Rake Face given Cutting Force and Thrust Force
Created Side cutting edge angle for given width of cut
Created Width of cut for given side cutting edge angle
15 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
Created Convective heat transfer to surface
Created Coefficient of drag equation with angle of attack
Created Coefficient of drag equation with coefficient of normal force
Created Coefficient of lift equation with angle of attack
Created Coefficient of lift equation with coefficient of normal force
Created Drag force with angle of attack
Created Exact normal shock wave maximum coefficient of pressure
Created Force Exerted on Surface given Static Pressure
Created Lift force with angle of attack
Created Mass Flux Incident on Surface Area
Created Maximum Pressure coefficient
Created Modified Newtonian Law
Created Pressure coefficient for slender 2D bodies
Created Pressure coefficient for slender bodies of revolution
Created Time rate of change of momentum of mass flux
Verified Characteristic Mach number
Verified Critical speed of sound from Prandtl relation
Verified Mach Number behind Shock
Verified Prandtl Condition
16 More Normal Shock Waves Calculators
Verified Length of Crest of Weir or Notch
Verified Time required to Empty Reservoir
4 More Notches and Weirs Calculators
Verified Component of Upstream Mach normal to oblique shock
18 More Oblique Shock and Expansion Waves Calculators
Created Coefficient of pressure derived from oblique shock theory
Created Density ratio when Mach become infinite
Verified Dynamic pressure for given specific heat ratio and Mach number
Created Exact Density Ratio
Created Exact pressure ratio
Created Non-dimensional pressure coefficient
Created Parallel upstream flow components after shock as Mach tends to infinite
Created Perpendicular upstream flow components behind the shock wave
Created Pressure Coefficient behind Oblique Shock Wave
Created Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number
Created Pressure ratio when Mach becomes infinite
Created Temperature ratio when Mach becomes infinite
Created Temperature ratios
Created Velocity of sound using dynamic pressure and density
Created Wave angle for small deflection angle
Verified Area at vena contracta for discharge and constant head
Verified Area of Mouthpiece in Borda's Mouthpiece Running Free
Verified Area of Mouthpiece in Borda's Mouthpiece Running Full
Verified Area of Orifice given Time of Emptying Hemispherical Tank
Verified Coefficient of Contraction given Area of Orifice
Verified Head of Liquid above Centre of Orifice
Verified Horizontal distance for coefficient of velocity and vertical distance
Verified Vertical distance for coefficient of velocity and horizontal distance
8 More Orifices and Mouthpieces Calculators
Verified Interface temperature of composite wall of 2 layers given outer surface temperature
Verified Total Thermal Resistance of Plane Wall with Convection on both Sides
20 More Plane walls Calculators
Verified Shaft brake power for reciprocating engine-propeller combination
2 More Power Available and Maximum Velocity Calculators
Verified Power required for given aerodynamic coefficients
Verified Thrust of aircraft required for given required power
Verified Weight of aircraft for given required power
7 More Power Required for Level Unaccelerated Flight Calculators
Verified Efficiency of power transmission in flow through pipes
2 More Power Transmission Efficiency Calculators
Verified Pressure at upstream point on streamline by Bernoulli's equation
Verified Pressure Coefficient
Verified Static pressure in incompressible flow
Verified Surface pressure coefficient for non-lifting flow over circular cylinder
9 More Pressure Calculators
Verified Radial velocity for non-lifting flow over circular cylinder
Verified Endurance for given Lift-to-Drag ratio of Jet Airplane
Verified Lift-to-Drag ratio for given Endurance of Jet Airplane
Verified Range of Jet Airplane
Verified Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
Verified Thrust-Specific Fuel Consumption for given Range of Jet Airplane
2 More Range and Endurance of Jet Airplane Calculators
Verified Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
9 More Range and Endurance of Propeller-Driven Airplane Calculators
Verified Rate of Climb
Verified Rate of Climb for given excess power
Verified Weight of aircraft for given excess power
7 More Rate of Climb Calculators
Created Chord length for flat plate case
Created Local Reynolds number
Created Local turbulent skin-friction coefficient for incompressible flow
Created Mach number at reference temperature
Created Overall skin-friction drag coefficient
Created Overall skin-friction drag coefficient for incompressible flow
Created Reference temperature equation
Created Reynolds number for chord length
Created Reynolds number for chord length using Overall skin-friction drag coefficient
Created Stanton Number obtained from classical theory
Created Static density of plate using chord length for flat plate case
Created Static velocity of plate using chord length for flat plate case
Created Static viscosity of plate using chord length for flat plate case
Created Turbulent flat-plate skin-friction coefficient
Created Wall temperature using reference temperature
Created Lattice Constant of SCC
Created Total volume of atoms in SCC
Created Coefficient of pressure equation using specific heat ratio
Created curvilinear grid location equation
Created Density equation using enthalpy and pressure
Created Enthalpy equation using coefficient of pressure for calorically perfect gas
Created Enthalpy equation using pressure and density
Created Enthalpy equation using specific heat ratio
Created Free stream enthalpy
Created local shock-layer thickness
Created pressure equation using Enthalpy and density
Created total enthalpy equation using specific heat ratio and velocities
Created Total specific enthalpy
Verified Heat flow rate through spherical wall
Verified Thermal Resistance of Spherical Wall
9 More Spheres Calculators
Verified Radius of the cylinder for a single stagnation point
3 More Stagnation Points Calculators
Verified Stagnation temperature considering the compressible fluid flow
1 More Stagnation Temperature Calculators
Verified Elevator chord length for given stick force
Verified Elevator Stick force for given gearing ratio
5 More Stick Forces Calculators
Verified Stream function for flow over Rankine oval
Verified Stream function for uniform incompressible flow in polar coordinates
7 More Stream Function Calculators
Verified Angle of incidence of wing
Verified Mean aerodynamic chord for given tail pitching moment coefficient
19 More Tail Contribution Calculators
Verified Horizontal tail volume ratio for given pitching moment coefficient
Verified Tail Efficiency for given tail volume ratio
Verified Tail lift coefficient for given tail volume ratio
Verified Tail Pitching moment coefficient for given tail volume ratio
10 More Tail Contribution Contd Calculators
Verified Liftoff velocity for given stall velocity
13 More Takeoff Performance Calculators
Verified Tangential velocity for 2-D Vortex flow
Verified Tangential velocity for lifting flow over circular cylinder
1 More Tangential Velocity Calculators
Created Thrust force for given frictional force along tool rake face, cutting force & normal rake angle
Created Thrust Force given Cutting Force and Normal Rake Angle
2 More Thrust Force Calculators
Verified Minimum Thrust required for given weight
Verified Thrust-to-weight ratio
10 More Thrust Required for Level Unaccelerated Flight Calculators
Verified Time of Emptying Hemispherical Tank
2 More Time of Emptying Calculators
Verified Total torque measured by strain in rotating cylinder method
4 More Torque Required Calculators
Verified Shear stress developed for turbulent flow in pipes
Verified Shear velocity for turbulent flow in pipes
16 More Turbulent flow Calculators
Verified Weight of aircraft during level turn
11 More Turning Flight Calculators
Verified Angular speed of outer cylinder in rotating cylinder method
Verified Maximum velocity at any radius with a velocity, and radius of pipe
Verified Velocity of piston or body for movement of piston in dash-pot
1 More Velocity Calculators
Verified Freestream velocity for a single stagnation point
Verified Tangential velocity for single stagnation point
4 More Velocity Calculators
Verified Velocity at the outlet for head loss at the exit of pipe
Verified Velocity of fluid for head loss due to obstruction in a pipe
Verified Velocity of liquid at vena-contracta
6 More Velocity of Flow Calculators
Verified Velocity of sound wave in terms of an adiabatic process
Verified Velocity of sound wave in terms of isothermal process
3 More Velocity of Sound Wave Calculators
Verified Velocity potential for 2-D doublet flow
Verified Velocity potential for 2-D source flow
Verified Velocity potential for uniform incompressible flow in polar coordinates
2 More Velocity Potential Calculators
Verified Viscosity of fluid or oil for movement of piston in dash-pot
Verified Viscosity of fluid or oil in rotating cylinder method
3 More Viscosity of Fluid Calculators
Verified Radius of pipe from maximum velocity and velocity at any radius
19 More Viscous flow Calculators
Created Aerodynamic heating to surface
Created Chapman–Rubesin factor
Created Coefficient of friction using Stanton equation for incompressible flow
Created Density calculation using Chapman–Rubesin factor
Created Internal Energy for Hypersonic Flow
Created Non dimensional internal energy parameter
Created Non dimensional internal energy parameter using wall-to-freestream temperature ratio
Created Non dimensional static enthalpy
Created Stanton equation using Overall skin friction coefficient for incompressible flow
Created Stanton number for incompressible flow
Created Static Density calculation using Chapman–Rubesin factor
Created Static enthalpy
Created Static viscosity calculation using Chapman–Rubesin factor
Created Thermal conductivity using Prandtl number
Created Viscosity calculation using Chapman–Rubesin factor
Created Wall temperature calculation using internal energy change Let Others Know