Calculators Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu
https://www.linkedin.com/in/sanjay-krishna-80a7b913b/
299
Formulas Created
200
Formulas Verified
109
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 109 different categories till date.
Verified Interface Temperature of Composite Wall of 2 Layers given Outer Surface Temperature
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7 More 2 Layers Calculators
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Verified Airspeed Measurement by Pitot Tube
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9 More Aerodynamic Measurements and Wind Tunnel Testing Calculators
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Verified Sidewash angle
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9 More Aerodynamic Parameters Calculators
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Verified Velocity along roll axis for small sideslip angle
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Verified Velocity along yaw axis for small angle of attack
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Verified Yawing moment
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Verified Yawing moment coefficient
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14 More Aircraft Dynamics Nomenclature Calculators
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Created Non-Dimensional Density
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Created Non-Dimensional Density for High Mach Number
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Created Non-Dimensional Parallel Velocity Component for High Mach Number
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Created Non-Dimensional Perpendicular Velocity Component for High Mach Number
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Created Non-Dimensional Pressure
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Created Non-Dimensional Pressure for High Mach Number
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Created Non-Dimensional Radius for Hypersonic Vehicles
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Created Slenderness Ratio with Cone Radius for Hypersonic Vehicle
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Created Transformed Conical Variable
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Created Transformed Conical Variable with Cone Angle in Hypersonic Flow
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Created Transformed Conical Variable with Wave Angle
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Created Adiabatic Wall Enthalpy over Flat Plate using Stanton Number
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Created Coefficient of Drag over Flat under Freestream Flow Conditions
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Created Drag Force over Flat Plate
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Created Free Stream Enthalpy over Flat Plate with Freestream Conditions
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Created Free Stream Velocity over Flat Plate using Drag Force
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Created Free Stream Velocity over Flat Plate with Freestream Conditions
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Created Freestream Density over Flat Plate using Stanton Number
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Created Freestream Density over Flat under Freestream Flow Conditions
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Created Freestream Stanton Number for Flat Plate
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Created Freestream Velocity over Flat Plate using Stanton Number
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Created Local Heat Transfer over Flat Plate using Stanton Number
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Created Pressure Ratio for Insulated Flat Plate, Strong Interaction
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Created Pressure Ratio for Insulated Flat Plate, Weak Interaction
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Created Total Enthalpy over Flat Plate with Freestream Conditions
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Created Wall Enthalpy over Flat Plate using Stanton Number
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Created Aerodynamic Heating to Surface
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Created Chapman-Rubesin Factor
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Created Coefficient of Friction using Stanton Equation for Incompressible Flow
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Created Density Calculation using Chapman-Rubesin Factor
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Created Internal Energy for Hypersonic Flow
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Created Non Dimensional Internal Energy Parameter
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Created Non Dimensional Internal Energy Parameter using Wall-to-Freestream Temperature Ratio
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Created Non Dimensional Static Enthalpy
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Created Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow
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Created Stanton Number for Incompressible Flow
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Created Static Density Calculation using Chapman-Rubesin Factor
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Created Static Enthalpy
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Created Static Viscosity Calculation using Chapman-Rubesin Factor
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Created Thermal Conductivity using Prandtl Number
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Created Viscosity Calculation using Chapman-Rubesin Factor
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Created Wall Temperature Calculation using Internal Energy Change
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Verified Thermal Conductance for given Thermal Resistance
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Verified Total Thermal Resistance for Conduction through Two Resistances in Parallel
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4 More Basics of HMT Calculators
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Verified Pressure at Upstream Point by Bernoulli's Equation
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Verified Pressure Coefficient
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Verified Static Pressure in Incompressible Flow
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3 More Bernoulli's Equation and Pressure Concepts Calculators
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Created Pressure Coefficient Combined with Blast Wave for Shuttle
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Created Pressure Coefficient Combined with Blast Wave for Shuttle at Angle of Attack
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Created Pressure Coefficient for Blast Wave Theory
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Created Pressure Coefficient for Blast Wave Theory at Very High Values of Mach
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Created Pressure Coefficient for Blunt-Nosed Cylinder
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Created Pressure Coefficient for Blunt-Nosed Plate
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Created Atomic Radius in BCC
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Created Lattice Constant of BCC
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Created Total Volume of Atoms in BCC
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Verified Tension in String given Coefficient of Friction of Horizontal Plane
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1 More Body Lying on Rough Horizontal Plane Calculators
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Verified Acceleration of System with Bodies One Hanging Free, Other Lying on Rough Inclined Plane
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Verified Coefficient of Friction given Tension
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Verified Inclination of Plane for given Frictional Force
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Verified Mass of Body B given Frictional Force
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Verified Tension in String given Coefficient of Friction of Inclined Plane
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2 More Body Lying on Rough Inclined Plane Calculators
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Verified Frictional Force on Body A
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5 More Body Lying on Rough Inclined Plane Calculators
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Verified Acceleration of System with Bodies One Hanging Free and Other Lying on Smooth Inclined Plane
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Verified Angle of Inclination given Acceleration
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Verified Angle of Inclination given Tension
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1 More Body Lying on Smooth Inclined Plane Calculators
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Verified Acceleration of System with Bodies Connected by String and Lying on Smooth Inclined Planes
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Verified Tension in String if Both Bodies are Lying on Smooth Inclined Planes
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2 More Body Lying on Smooth Inclined Plane Calculators
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Verified Area of Surface for Average Drag Coefficient
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Verified Distance from Leading Edge
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Verified Distance from Leading Edge for Blasius's Solution
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Verified Length of Plate for Reynold Number
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Verified Reynold Number at End of Plate
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Verified Reynold Number for Drag Coefficient in Blasius's Solution
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Verified Shear Stress at Boundary for Turbulent Boundary Layer over Flat Plate
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Verified Thickness of Boundary Layer
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Verified Thickness of Boundary Layer for Blasius's Solution
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Verified Velocity of Fluid for Reynold Number
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11 More Boundary Layer Flow Calculators
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Verified Angle of heel for metacentric height in experimental method
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Verified Meta-centric height in experimental method
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Verified Movable weight for metacentric height in experimental method
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8 More Buoyancy Calculators
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Verified Rate of Climb
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Verified Rate of Climb for given excess power
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Verified Weight of aircraft for given excess power
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13 More Climbing Flight Calculators
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Verified Pressure Ratio for Maximum Flow Rate through Nozzle
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9 More Compressible Flow Parameters Calculators
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Created Density before Shock Formation for Compression Wave
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Created New Pressure after Shock Formation for Compression Wave
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Created Temperature Ratio for Unsteady Compression Waves
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Created Emissivity
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Created Freestream Density
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Created Freestream Velocity
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Created Reference Viscosity
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7 More Computational Fluid Dynamic Solutions Calculators
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Created Fourier's Law of Heat Conduction
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5 More Conduction Calculators
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Verified Total Thermal Resistance of 2 Cylindrical Resistances Connected in Series
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Verified Total Thermal Resistance of 3 Cylindrical Resistances Connected in Series
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Verified Total Thermal Resistance of Cylindrical Wall with Convection on Both Sides
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11 More Conduction in Cylinder Calculators
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Verified Total Thermal Resistance of Plane Wall with Convection on Both Sides
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7 More Conduction in Plane Wall Calculators
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Verified Heat Flow Rate through Spherical Wall
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Verified Thermal Resistance of Spherical Wall
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9 More Conduction in Sphere Calculators
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Created Atomic Packing Factor
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Created Cutting Force given Thrust Force and Normal Rake Angle
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5 More Cutting Force Calculators
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Verified Radius of Cylinder for Single Stagnation Point
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6 More Cylinder Properties Calculators
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Created Boltzmann Constant for Cylindrical Blast Wave
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Created Modified Energy for Cylindrical Blast Wave
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Created Modified Pressure Equation for Cylindrical Blast Wave
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Created Modified Radial Coordinate Equation for Cylindrical Blast Wave
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Created Pressure for Cylindrical Blast Wave
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Created Pressure Ratio for Blunt Cylinder Blast Wave
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Created Radial Coordinate of Cylindrical Blast Wave
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Created Simplified Pressure Ratio for Blunt Cylinder Blast Wave
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Created Nusselt's Number with Reynolds Number, Stanton Number and Prandtl Number
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Created Prandtl Number with Reynolds Number, Nusselt's Number, and Stanton Number
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Created Reynolds Number for given Nusselt's Number, Stanton Number and Prandtl Number
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Created Stanton Number with Reynolds Number, Nusselt's Number, Stanton Number and Prandtl Number
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Verified Diameter of Pipe for Difference in Pressure in Viscous Flow
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Verified Diameter of Pipe for Head Loss due to Friction in Viscous Flow
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Verified Diameter of Pipe for Loss of Pressure Head in Viscous Flow
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Verified Diameter of Pipe from Maximum Velocity and Velocity at Any Radius
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Verified Length of Pipe for Difference of Pressure in Viscous Flow
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Verified Length of Pipe for Head Loss due to Friction in Viscous Flow
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Verified Length of Pipe for Loss of Pressure Head in Viscous Flow
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12 More Dimensions and Geometry Calculators
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Verified Coefficient of Discharge for Time Required to Empty Reservoir
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Verified Time Required to Empty Reservoir
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15 More Discharge Calculators
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Verified Velocity Potential for 2-D Doublet Flow
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1 More Doublet Flow Calculators
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Verified Enthalpy behind Normal Shock from Normal Shock Energy Equation
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Verified Mach Number behind Shock
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Verified Velocity behind Normal Shock by Normal Shock Momentum Equation
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12 More Downstream Shock Waves Calculators
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Verified Coefficient of drag for sphere in Oseen formula when Reynolds number is between 0.2 and 5
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Verified Coefficient of drag for sphere in stoke's law when Reynolds number is less than 0.2
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Verified Drag Force for body moving in Fluid of Certain Density
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Verified Total Drag force on Sphere
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7 More Drag and Forces Calculators
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Created Emissivity per Unit Mole
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Created Kinetic Energy per Mole
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Created Kinetic Energy per Mole using Molar Volume
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Created Kinetic Energy per Mole using Temperature of Gas
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Created Mean Free Path of Single-Species Gas
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Created Mean Free Path using Number Density
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Created Molar Volume using Kinetic Energy per Mole
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Created Number Density
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Created Pressure of Gas using Number Density
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Created Pressure using Kinetic Energy per Mole
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Created Pressure using Molar Volume
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Created Specific Gas Constant using Kinetic Energy per Mole
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Created Temperature of Gas using Emissivity per Unit Mole
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Created Temperature of Gas using Kinetic Energy per Mole
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Created Volume of Gas
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Created Detachment Distance of Cylinder Wedge Body Shape
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Created Detachment Distance of Sphere Cone Body Shape
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Created Grid Point Calculation for Shock Waves
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Created Local Shock Velocity Equation
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Created Mach Wave behind Shock
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Created Mach Wave behind Shock with Mach Infinity
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Created Nose Radius of Cylinder-Wedge
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Created Nose Radius of Sphere Cone
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Created Pressure Ratio for Unsteady Waves
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Created Ratio of New and Old Temperature
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Created Density before Shock Formation for Expansion Wave
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Created New Pressure after Shock Formation, Subtracted to Velocity for Expansion Wave
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Created Pressure Ratio for Unsteady Waves with Subtracted Induced Mass Motion for Expansion Waves
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Created Ratio of New and Old Temperature for Expansion Waves
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Created Temperature Ratio for Unsteady Expansion Wave
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Created Atomic Radius in FCC
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Created Lattice Constant of FCC
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Created Volume of Atoms in FCC
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Verified Loss of Head Due to Friction
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Verified Loss of Pressure Head for Viscous Flow through Circular Pipe
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Verified Viscosity of Fluid or Oil for Movement of Piston in Dash-Pot
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Verified Viscosity of Fluid or Oil in Rotating Cylinder Method
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9 More Flow Analysis Calculators
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Verified Head of Liquid above Centre of Orifice
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5 More Flow Head Calculators
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Verified Bazin's constant
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Verified Chezy's constant considering Bazin formula
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Verified Chezy's constant considering velocity
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Verified Critical depth considering flow in open channels
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Verified Critical depth considering minimum specific energy
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Verified Critical Depth using Critical Velocity
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Verified Critical velocity considering flow in open channels
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Verified Discharge per unit width considering flow in open channels
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Verified Hydraulic mean depth considering Bazin formula
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Verified Hydraulic mean depth using Chezy's formula
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Verified Minimum Specific Energy using Critical Depth
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Verified Velocity of Chezy's formula
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7 More Flow in Open Channels Calculators
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Verified Boundary Layer Thickness for Turbulent Flow
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Verified Center of Pressure Location for Cambered Airfoil
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Verified Skin Friction Drag Coefficient for Flat Plate in Laminar Flow
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Verified Skin Friction Drag Coefficient for Flat Plate in Turbulent Flow
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4 More Flow over Airfoils Calculators
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Verified Coefficient of Discharge given Time of Emptying Hemispherical Tank
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Verified Discharge in Borda's Mouthpiece Running Free
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Verified Discharge in Borda's Mouthpiece Running Full
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Verified Discharge in Convergent-Divergent Mouthpiece
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7 More Flow Rate Calculators
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Verified Coefficient of contraction for sudden contraction
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Verified Retarding force for gradual closure of valves
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Verified Time taken by pressure wave to travel
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Verified Velocity at Outlet for Head Loss at Exit of Pipe
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Verified Velocity of Fluid for Head Loss due to Obstruction in Pipe
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Verified Velocity of liquid at vena-contracta
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11 More Flow Regime Calculators
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Verified Angular Speed of Outer Cylinder in Rotating Cylinder Method
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Verified Maximum Velocity at any Radius using Velocity
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Verified Total Torque Measured by Strain in Rotating Cylinder Method
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Verified Velocity at Any Radius given Radius of Pipe, and Maximum Velocity
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Verified Velocity of Piston or Body for Movement of Piston in Dash-Pot
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16 More Fluid Flow and Resistance Calculators
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Verified Freestream Velocity for single Stagnation Point
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Verified Tangential velocity for single stagnation point
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7 More Fluid Parameters and Characteristics Calculators
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Created Coefficient of friction for given friction angle
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Created Coefficient of friction for given thrust force, cutting force and normal rake angle
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Created Coefficient of Friction given Forces Normal and along Tool Rake Face
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3 More Forces and Friction Calculators
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Verified Length of Crest of Weir or Notch
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9 More Geometric DImension Calculators
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Verified Area at vena contracta for discharge and constant head
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Verified Area of Mouthpiece in Borda's Mouthpiece Running Free
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Verified Area of Mouthpiece in Borda's Mouthpiece Running Full
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Verified Area of Orifice given Time of Emptying Hemispherical Tank
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Verified Coefficient of Contraction given Area of Orifice
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Verified Horizontal distance for coefficient of velocity and vertical distance
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Verified Vertical distance for coefficient of velocity and horizontal distance
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1 More Geometric Dimensions Calculators
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Verified Maximum Area of Obstruction in Pipe
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6 More Geometric Property Calculators
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Created Area of shear plane for given shear angle, width of cut and uncut chip thickness
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Created Side cutting edge angle for given width of cut
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Created Width of cut for given side cutting edge angle
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5 More Geometry and Dimensions Calculators
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Verified Lift Force for given Glide Angle
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Verified Lift-to-drag ratio for given glide angle
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4 More Gliding Flight Calculators
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Verified Mayer's Formula
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Verified Ratio of Stagnation and Static Density
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Verified Ratio of Stagnation and Static Temperature
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15 More Governing Equations and Sound Wave Calculators
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Verified Lift Coefficient for given wing loading and turn radius
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Verified Wing loading for given turn radius
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27 More High Load Factor Maneuver Calculators
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Created Blunt-Nosed Radial Coordinate Flat Plate (First Approximation)
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Created Forces Acting on Body along Flight Path
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Created Forces Acting Perpendicular to Body on Flight Path
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Created Pressure Ratio of Blunt-Nosed Cylinder (First Approximation)
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Created Radial Coordinate of Blunt-Nosed Cylinder (First Approximation)
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Created Radius for Cylinder-Wedge Body Shape
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Created Radius for Sphere-Cone Body Shape
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Created Radius of Curvature for Cylinder Wedge Body Shape
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Created Radius of Curvature for Sphere Cone Body Shape
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Created Axial Force Coefficient
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Created Coefficient of Drag
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Created Coefficient of Pressure with Similarity Parameters
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Created Deflection Angle
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Created Drag Force
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Created Dynamic Pressure
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Created Dynamic Pressure given Coefficient of Lift
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Created Hypersonic Similarity Parameter
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Created Lift Coefficient
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Created Lift Force
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Created Mach Number with Fluids
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Created Mach Ratio at High Mach Number
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Created Moment Coefficient
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Created Newtonian Sine Squared Law for Pressure Coefficient
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Created Normal Force Coefficient
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Created Pressure Ratio for High Mach Number
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Created Pressure Ratio having High Mach Number with Similarity Constant
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Created Shear-Stress Distribution
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Created Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle
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1 More Hypersonic Flow Parameters Calculators
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Created Dynamic Viscosity around Wall
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Created Local Shear Stress at Wall
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Created Local Skin-Friction Coefficient
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Created Skin Friction Coefficient for Incompressible Flow
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Created Static Density Equation using Skin Friction Coefficient
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Created Static Velocity Equation using Skin Friction Coefficient
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Created Static Viscosity Relation using Temperature of Wall
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Created Change in Velocity for Hypersonic Flow in X Direction
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Created Coefficient of Pressure with Slenderness Ratio
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Created Coefficient of Pressure with Slenderness Ratio and Similarity Constant
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Created Constant G used for Finding Location of Perturbed Shock
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Created Density Ratio with Similarity Constant having Slenderness Ratio
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Created Distance from Tip of Leading Edge to Base
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Created Doty and Rasmussen- Normal Force Coefficient
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Created Inverse of Density for Hypersonic Flow
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Created Inverse of Density for Hypersonic Flow using Mach Number
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Created Rasmussen Closed Form Expression for Shock Wave Angle
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Created Similarity Constant Equation using Wave Angle
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Created Similarity Constant Equation with Slenderness Ratio
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Created Boundary-Layer Momentum Thickness using Reynolds Number at Transition Point
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Created Eddy Viscosity Calculation
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Created Local Mach Number using Reynolds Number Equation at Transition Region
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Created Location of Transition Point
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Created Prandtl Number of Transition Flow
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Created Reynolds Number Equation using Boundary-Layer Momentum Thickness
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Created Reynolds Number Equation using Local Mach Number
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Created Specific Heat at Constant Pressure for Transient Flow
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Created Static Density at Transition Point
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Created Static Density Equation using Boundary-Layer Momentum Thickness
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Created Static Velocity at Transition Point
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Created Static Velocity using Boundary-Layer Momentum Thickness
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Created Static Viscosity at Transition Point
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Created Static Viscosity Equation using Boundary-Layer Momentum Thickness
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Created Thermal Conductivity of Transition Flow
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Created Transition Reynolds Number
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Created Large Mach Number over Flat Plate using Static Temperature and Wall Temperature
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Created Mach Number over Flat Plate using Static Temperature and Wall Temperature
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Created Pressure Ratio for Cold-Wall Case Strong Interaction
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Created Pressure Ratio for Cold-Wall Case Weak Interaction
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Created Total Temperature over Flat Plate under Viscous Mach Flow
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Created Total Temperature over Flat Plate under Viscous Very High Mach Flow
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Created Viscosity of Wall using Wall Temperature and Static Temperature
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Created Wall Density of Fluid over Flat Plate
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Verified Radius of Rankine circle
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22 More Incompressible Flow Characteristics Calculators
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Verified Endurance for given Lift-to-Drag ratio of Jet Airplane
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Verified Lift-to-Drag ratio for given Endurance of Jet Airplane
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Verified Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
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Verified Range of Jet Airplane
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Verified Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
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Verified Thrust-Specific Fuel Consumption for given Range of Jet Airplane
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12 More Jet Airplane Calculators
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Verified Actual Discharge in Venturimeter
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Verified Difference in Pressure Head for heavier Liquid in Manometer
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Verified Difference in pressure head for light liquid in manometer
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Verified Height or depth of paraboloid for volume of air
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Verified Total Pressure Force at Bottom of Cylinder
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Verified Total pressure force on top of cylinder
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Verified Velocity at any point for coefficient of pitot-tube
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10 More Kinematics of Flow Calculators
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Verified Lift Per Unit Span by Kutta-Joukowski Theorem
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3 More Kutta-Joukowski Lift Theorem Calculators
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Created Newtonian Dynamic Pressure
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Created Newtonian Pressure Distribution over Surface using Cosine Angle
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Created Nusselt Number at Stagnation Point
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Created Nusselt Number for Stagnation Point on Blunt Body
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Created Reynolds Analogy Factor in Finite Deference Method
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Created Reynolds Analogy for Stanton Number in Finite Difference Method
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Created Stagnation Pressure
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Verified Landing ground roll distance
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4 More Landing Calculators
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Verified Circulation for Single Stagnation Point
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15 More Lift and Circulation Calculators
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Verified Coefficient of Drag for given thrust and weight
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Verified Lift-induced drag coefficient for given required thrust
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17 More Lift and Drag Requirements Calculators
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Verified Tangential Velocity for Lifting Flow over Circular Cylinder
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9 More Lifting Flow over Cylinder Calculators
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Created Adiabatic Wall Enthalpy using Stanton Number
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Created Enthalpy of Wall using Stanton Number
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Created Local Heat Transfer Rate Calculation using Stanton Number
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Created Local Heat Transfer Rate using Nusselt's Number
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Created Nusselt Number for Hypersonic Vehicle
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Created Stanton Number for Hypersonic Vehicle
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Created Static Density Equation using Stanton Number
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Created Static Velocity using Stanton Number
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Created Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number
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Created Convective Heat Transfer to Surface
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Created Radiative Heat Transfer to Surface Stemming from Thermal Radiation
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Verified Absolute Temperature for Velocity of Sound Wave in Isothermal Process
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Verified Absolute Temperature for Velocity of Sound Wave using Adiabatic Process
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Verified Density of Fluid considering Velocity at Outlet of Orifice
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Verified Velocity of Sound Wave using Adiabatic Process
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Verified Velocity of Sound Wave using Isothermal Process
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2 More Multiphase Compressible Flow Calculators
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Created Coefficient of Drag Equation with Angle of Attack
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Created Coefficient of Drag Equation with Coefficient of Normal Force
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Created Coefficient of Lift Equation with Angle of Attack
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Created Coefficient of Lift Equation with Coefficient of Normal Force
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Created Drag Force with Angle of Attack
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Created Exact Normal Shock Wave Maximum Coefficient of Pressure
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Created Force Exerted on Surface given Static Pressure
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Created Lift Force with Angle of Attack
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Created Mass Flux Incident on Surface Area
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Created Maximum Pressure Coefficient
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Created Modified Newtonian Law
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Created Pressure Coefficient for Slender 2D Bodies
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Created Pressure Coefficient for Slender Bodies of Revolution
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Created Time Rate of Change of Momentum of Mass Flux
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Created Non Dimensional Change in Hypersonic Disturbance Velocity in x Direction
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Created Non Dimensional Change in Hypersonic Disturbance Velocity in y Direction
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Created Non Dimensional Pressure Equation with Slenderness Ratio
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Created Non Dimensional Velocity Disturbance in y Direction in Hypersonic Flow
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Created Non Dimensionalised Time
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Verified Radial Velocity for Non-Lifting Flow over Circular Cylinder
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Verified Surface Pressure Coefficient for Non-Lifting Flow over Circular Cylinder
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8 More Nonlifting Flow over Cylinder Calculators
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Verified Characteristic Mach Number
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Verified Critical Speed of Sound from Prandtl Relation
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Verified Downstream Velocity using Prandtl Relation
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Verified Upstream Velocity using Prandtl Relation
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3 More Normal Shock Relations Calculators
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Verified Component of Upstream Mach Normal to Oblique Shock
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9 More Oblique Shock Calculators
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Created Coefficient of Pressure Derived from Oblique Shock Theory
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Created Density Ratio when Mach Becomes Infinite
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Verified Dynamic Pressure for given Specific Heat Ratio and Mach Number
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Created Exact Density Ratio
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Created Exact Pressure Ratio
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Created Non-Dimensional Pressure Coefficient
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Created Parallel Upstream Flow Components after Shock as Mach Tends to Infinite
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Created Perpendicular Upstream Flow Components behind Shock Wave
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Created Pressure Coefficient behind Oblique Shock Wave
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Created Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number
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Created Pressure Ratio when Mach becomes Infinite
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Created Temperature Ratio when Mach Becomes Infinite
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Created Temperature Ratios
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Created Velocity of Sound using Dynamic Pressure and Density
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Created Wave Angle for Small Deflection Angle
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Created Blunt-Nosed Flat Plate Pressure Ratio (First Approximation)
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Created Coefficient of Drag Equation using Energy Released from Blast Wave
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Created Creation Pressure for Planar Blast Wave
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Created Energy for Blast Wave
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Created Pressure Ratio for Blunt Slab Blast Wave
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Created Radial Coordinate for Planar Blast Wave
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Created Radial Coordinate of Blunt Slab Blast Wave
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Created Time Required for Blast Wave
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Verified Efficiency of power transmission in flow through pipes
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Verified Power Lost ue to Sudden Enlargement
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Verified Power transmission through pipes
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2 More Power Transmission Calculators
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Verified Velocity at Altitude
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16 More Preliminary Aerodynamics Calculators
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Verified Difference in liquid level in three compound pipes with same friction coefficient
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Verified Head available at Base of Nozzle
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Verified Head Loss due to Friction for Efficiency of Power Transmission
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Verified Loss of head at exit of pipe
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Verified Loss of Head due to Obstruction in Pipe
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Verified Total head at inlet of pipe for head available at base of nozzle
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Verified Total head available at inlet of pipe for efficiency of power transmission
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7 More Pressure and Flow Head Calculators
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Verified Shaft brake power for reciprocating engine-propeller combination
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20 More Propeller-Driven Airplane Calculators
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Created Chord Length for Flat Plate Case
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Created Local Reynolds Number
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Created Local Turbulent Skin-Friction Coefficient for Incompressible Flow
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Created Mach Number at Reference Temperature
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Created Overall Skin-Friction Drag Coefficient
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Created Overall Skin-Friction Drag Coefficient for Incompressible Flow
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Created Reference Temperature Equation
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Created Reynolds Number for Chord Length
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Created Reynolds Number for Chord Length using Overall Skin-Friction Drag Coefficient
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Created Stanton Number Obtained from Classical Theory
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Created Static Density of Plate using Chord Length for Flat Plate Case
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Created Static Velocity of Plate using Chord Length for Flat Plate Case
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Created Static Viscosity of Plate using Chord Length for Flat Plate Case
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Created Turbulent Flat-Plate Skin-Friction Coefficient
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Created Wall Temperature using Reference Temperature
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Created Force acting Normal to Rake Face given Cutting Force and Thrust Force
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5 More Resultants and Stress Calculators
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Created Atomic Radius in SCC
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Created Lattice Constant of SCC
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Created Total Volume of Atoms in SCC
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Verified Stream Function for Flow over Rankine Oval
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Verified Velocity Potential for 2-D Source Flow
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5 More Source Flow Calculators
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Created Coefficient of Pressure Equation using Specific Heat Ratio
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Created Curvilinear Grid Location Equation
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Created Density Equation using Enthalpy and Pressure
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Created Enthalpy Equation using Coefficient of Pressure for Calorically Perfect Gas
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Created Enthalpy Equation using Pressure and Density
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Created Enthalpy Equation using Specific Heat Ratio
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Created Free Stream Enthalpy
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Created Local Shock-Layer Thickness
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Created Pressure Equation using Enthalpy and Density
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Created Total Enthalpy Equation using Specific Heat Ratio and Velocities
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Created Total Specific Enthalpy
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Verified Stagnation Temperature considering Compressible Fluid Flow
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Verified Temperature of Fluid for Stagnation Temperature considering Compressible Fluid Flow
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6 More Stagnation Properties Calculators
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Created Static Density of Fluid over Flat Plate
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Created Static Temperature of Fluid over Flat Plate
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Created Static Temperature of Plate using Wall Viscosity
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Created Static Temperature over Flat Plate under Viscous, Very High Mach Flow
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Created Static Temperature over Flat Plate using Static Mach Number
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Created Static Viscosity using Wall Temperature and Static Temperature
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Verified Control stick length for given gearing ratio
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Verified Elevator Chord Length given Stick Force
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Verified Elevator Deflection Angle given Gearing Ratio
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Verified Elevator Stick Force given Gearing Ratio
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Verified Flight Velocity given Elevator Hinge Moment Coefficient
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Verified Hinge Moment Coefficient given Stick Force
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17 More Stick Forces and Hinge Moments Calculators
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Verified Horizontal tail volume ratio for given pitching moment coefficient
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Verified Mean aerodynamic chord for given tail pitching moment coefficient
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Verified Tail Efficiency for given tail volume ratio
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Verified Tail lift coefficient for given tail volume ratio
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Verified Tail Pitching moment coefficient for given tail volume ratio
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14 More Tail Contribution Calculators
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Verified Liftoff velocity for given stall velocity
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14 More Take-Off Calculators
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Verified Mach Angle
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18 More Thermodynamics and Governing Equations Calculators
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Verified Minimum Thrust required for given weight
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Verified Power required for given aerodynamic coefficients
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Verified Thrust of aircraft required for given required power
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Verified Thrust-to-weight ratio
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Verified Weight of aircraft for given required power
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14 More Thrust and Power Requirements Calculators
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Created Thrust force for given frictional force along tool rake face, cutting force and normal rake angle
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Created Thrust Force given Cutting Force and Normal Rake Angle
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2 More Thrust Force Calculators
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Verified Shear Stress Developed for Turbulent Flow in Pipes
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Verified Shear Velocity for Turbulent Flow in Pipes
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16 More Turbulent Flow Calculators
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Verified Weight of aircraft during level turn
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12 More Turning Flight Calculators
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Verified Stream Function for Uniform Incompressible Flow in Polar Coordinates
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Verified Velocity Potential for Uniform Incompressible Flow in Polar Coordinates
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2 More Uniform Flow Calculators
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Verified Enthalpy ahead of Normal Shock from Normal Shock Energy Equation
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Verified Velocity ahead of Normal Shock by Normal Shock Momentum Equation
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5 More Upstream Shock Waves Calculators
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Verified Coefficient of velocity
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Verified Time of Emptying Hemispherical Tank
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6 More Velocity and Time Calculators
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Verified Vertical tail efficiency
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23 More Vertical Tail Contribution Calculators
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Created Adiabatic Wall Enthalpy for Flat Plate
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Created Adiabatic Wall Enthalpy using Recovery Factor
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Created Aerodynamic Heating Equation for Stanton number
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Created Coefficient of Friction using Stanton Number for Flat Plate Case
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Created Drag per Unit Span
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Created Prandtl Number for Flat Plate with Viscous Flow
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Created Recovery Factor Calculation using Prandtl Number
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Created Recovery Factor for Flat Plate with Viscous Flow
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Created Recovery Factor using Temperature
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Created Skin-Friction Drag Coefficient
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Created Skin-Friction Drag for Flat Plate in Viscous Flow
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Created Stanton Number with Coefficient of Friction
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Created Static Density Equation using Aerodynamic Equation
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Created Static Velocity Equation using Aerodynamic Heating Equation
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Created Total Enthalpy in Inviscid Flow Outside Boundary Layer
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Verified Tangential Velocity for 2-D Vortex Flow
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2 More Vortex Flow Calculators
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Created Wall Temperature of Fluid over Flat Plate
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Created Wall Temperature of Plate using Wall Viscosity
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Created Wall Temperature over Flat Plate under Viscous, Very High Mach Flow
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Created Wall Temperature over Flat Plate using Static Mach Number
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Verified Angle of incidence of wing
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14 More Wing-Tail Contribution Calculators
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Verified Dynamic pressure at vertical tail for given vertical tail efficiency
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Verified Dynamic pressure at wing for given vertical tail efficiency
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11 More Wing-Tail Interaction Calculators
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