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Calculators Created by Maiarutselvan V
Maiarutselvan V
PSG College of Technology
(PSGCT)
,
Coimbatore
https://www.linkedin.com/in/maiarutselvan-v-ba5533149/
301
Formulas Created
274
Formulas Verified
100
Across Categories
List of Calculators by Maiarutselvan V
Following is a combined list of all the calculators that have been created and verified by Maiarutselvan V. Maiarutselvan V has created 301 and verified 274 calculators across 100 different categories till date.
2 Layers
(3)
Verified
Area of Composite Wall of 2 Layers
Go
Verified
Inner Surface Temperature of Composite Wall for 2 Layers in Series
Go
Verified
Thermal Resistance of Composite Wall with 2 Layers in Series
Go
5 More 2 Layers Calculators
Go
3 Layers
(4)
Verified
Area of Composite Wall of 3 Layers
Go
Verified
Inner Surface Temperature of Composite Wall of 3 Layers in Series
Go
Verified
Length of 3rd Layer of Composite Wall in Conduction through Walls
Go
Verified
Thermal Resistance of Composite Wall with 3 Layers in Series
Go
2 More 3 Layers Calculators
Go
Aerodynamic Measurements and Wind Tunnel Testing
(6)
Verified
Airspeed Measurement by Venturi
Go
Verified
Dynamic Pressure in Incompressible Flow
Go
Verified
Test Section Velocity by Manometric Height for Wind Tunnel
Go
Verified
Total Pressure in Incompressible Flow
Go
Verified
Wind Tunnel Pressure Difference by Manometer
Go
Verified
Wind Tunnel Test Section Velocity
Go
4 More Aerodynamic Measurements and Wind Tunnel Testing Calculators
Go
Aerodynamic Parameters
(1)
Verified
Sideslip Angle for Aircraft
Go
10 More Aerodynamic Parameters Calculators
Go
Aero-Thermal Dynamics
(9)
Verified
Aerodynamic Heating to Surface
Go
Verified
Chapman-Rubesin Factor
Go
Verified
Coefficient of Friction using Stanton Equation for Incompressible Flow
Go
Verified
Density Calculation using Chapman-Rubesin Factor
Go
Verified
Stanton Number for Incompressible Flow
Go
Verified
Static Density Calculation using Chapman-Rubesin Factor
Go
Verified
Static Viscosity Calculation using Chapman-Rubesin Factor
Go
Verified
Thermal Conductivity using Prandtl Number
Go
Verified
Viscosity Calculation using Chapman-Rubesin Factor
Go
7 More Aero-Thermal Dynamics Calculators
Go
Aircraft Dynamics Nomenclature
(5)
Verified
Normal Force Coefficient with Aerodynamic Normal Force
Go
Verified
Rolling Moment
Go
Verified
Rolling moment coefficient
Go
Verified
Velocity along Pitch Axis for Small Sideslip Angle
Go
Verified
Velocity along Roll Axis for Small Angle of Attack
Go
13 More Aircraft Dynamics Nomenclature Calculators
Go
Amplifier Characteristics
(1)
Verified
Current Gain of Amplifier in Decibels
Go
20 More Amplifier Characteristics Calculators
Go
Approximate Methods of Hypersonic Inviscid Flowfields
(3)
Verified
Non-Dimensional Pressure
Go
Verified
Non-Dimensional Pressure for High Mach Number
Go
Verified
Slenderness Ratio with Cone Radius for Hypersonic Vehicle
Go
8 More Approximate Methods of Hypersonic Inviscid Flowfields Calculators
Go
Approximate Results Applied to Hypersonic Vehicles
(5)
Verified
Coefficient of Drag over Flat under Freestream Flow Conditions
Go
Verified
Drag Force over Flat Plate
Go
Verified
Freestream Stanton Number for Flat Plate
Go
Verified
Local Heat Transfer over Flat Plate using Stanton Number
Go
Verified
Pressure Ratio for Insulated Flat Plate, Weak Interaction
Go
10 More Approximate Results Applied to Hypersonic Vehicles Calculators
Go
Blast Wave Part Theory
(1)
Verified
Pressure Coefficient for Blast Wave Theory
Go
5 More Blast Wave Part Theory Calculators
Go
Body Lying on Rough Inclined Plane
(2)
Verified
Coefficient of Friction given Frictional Force
Go
Verified
Frictional Force
Go
5 More Body Lying on Rough Inclined Plane Calculators
Go
Body Lying on Rough Inclined Plane
(5)
Verified
Acceleration of System given Mass of Body A
Go
Verified
Acceleration of System given Mass of Body B
Go
Verified
Frictional Force on Body B
Go
Verified
Tension in String given Mass of Body A
Go
Verified
Tension in String given Mass of Body B
Go
1 More Body Lying on Rough Inclined Plane Calculators
Go
Body Lying on Smooth Inclined Plane
(1)
Verified
Tension in String when One Body is Lying on Smooth Inclined Plane
Go
3 More Body Lying on Smooth Inclined Plane Calculators
Go
Body Lying on Smooth Inclined Plane
(2)
Verified
Angle of Inclination of Plane with Body A
Go
Verified
Angle of Inclination of Plane with Body B
Go
2 More Body Lying on Smooth Inclined Plane Calculators
Go
Boundary Layer Flow
(21)
Created
Area of Surface for Average Drag Coefficient
Go
Created
Average Coefficient of Drag for Drag Force
Go
Created
Coefficient of Drag for Blasius's Solution
Go
Created
Coefficient of Drag for Reynold Number
Go
Created
Distance from Leading Edge
Go
Created
Distance from Leading Edge for Blasius's Solution
Go
Created
Drag Force for Average Drag Coefficient
Go
Created
Drag Force on Plate
Go
Created
Freestream Velocity for Local Drag Coefficient
Go
Created
Length of Plate for Reynold Number
Go
Created
Local Drag Coefficient for Shear Stress
Go
Created
Reynold Number at End of Plate
Go
Created
Reynold Number for Drag Coefficient in Blasius's Solution
Go
Created
Reynold Number for Drag Force on Plate
Go
Created
Shear Stress at Boundary for Turbulent Boundary Layer over Flat Plate
Go
Created
Shear Stress for Local Drag Coefficient
Go
Created
Thickness of Boundary Layer
Go
Created
Thickness of Boundary Layer for Blasius's Solution
Go
Created
Velocity of Fluid for Reynold Number
Go
Created
Viscosity of Liquid for Drag Force on Plate
Go
Created
Width of Plate for Drag Force on Plate
Go
Buoyancy
(9)
Created
Angle of heel for metacentric height in experimental method
Go
Created
Centre of Buoyancy
Go
Created
Meta-centric height for time period of oscillation and radius of gyration
Go
Created
Meta-centric height in experimental method
Go
Created
Movable weight for metacentric height in experimental method
Go
Created
Radius of gyration for metacentric height and time period of oscillation
Go
Created
Time Period of Oscillation of Ship
Go
Created
Volume of body in fluid for metacentric height and BG
Go
Created
Volume of fluid displaced
Go
2 More Buoyancy Calculators
Go
Climbing Flight
(1)
Verified
Thrust available for given excess power
Go
15 More Climbing Flight Calculators
Go
Compressible Flow Parameters
(9)
Created
Bulk Modulus for Velocity of Sound Wave
Go
Created
Mach Angle for Compressible Fluid Flow
Go
Created
Mach Number for Compressible Fluid Flow
Go
Created
Pressure Ratio for Maximum Flow Rate through Nozzle
Go
Created
Velocity at Outlet of Nozzle for Maximum Flow Rate of Fluid
Go
Created
Velocity of Projectile of Mach Cone in Compressible Fluid Flow
Go
Created
Velocity of Sound Wave considering Mach Angle in Compressible Fluid Flow
Go
Created
Velocity of Sound Wave given Bulk Modulus
Go
Created
Velocity of Sound Wave given Mach Number for Compressible Fluid Flow
Go
1 More Compressible Flow Parameters Calculators
Go
Computational Fluid Dynamic Solutions
(2)
Verified
Emissivity
Go
Verified
Reference Viscosity
Go
9 More Computational Fluid Dynamic Solutions Calculators
Go
Conduction in Cylinder
(2)
Verified
Convection Resistance for Cylindrical Layer
Go
Verified
Length of Cylindrical Wall for given Heat Flow Rate
Go
12 More Conduction in Cylinder Calculators
Go
Conduction in Plane Wall
(3)
Verified
Inner Surface Temperature of Plane Wall
Go
Verified
Temperature at Distance x from Inner Surface in Wall
Go
Verified
Thermal Resistance of Wall
Go
5 More Conduction in Plane Wall Calculators
Go
Conduction in Sphere
(9)
Verified
Convection Resistance for Spherical Layer
Go
Verified
Heat Flow Rate through Spherical Composite Wall of 2 Layers in Series
Go
Verified
Inner Surface Temperature of Spherical Wall
Go
Verified
Outer Surface Temperature of Spherical Wall
Go
Verified
Thermal Resistance of Spherical Composite Wall of 2 Layers in Series with Convection
Go
Verified
Thickness of Spherical Wall to Maintain given Temperature Difference
Go
Verified
Total Thermal Resistance of Spherical Wall of 2 Layers without Convection
Go
Verified
Total Thermal Resistance of Spherical wall of 3 Layers without Convection
Go
Verified
Total Thermal Resistance of Spherical Wall with Convection on Both Side
Go
2 More Conduction in Sphere Calculators
Go
Cutting Force
(2)
Created
Cutting Force for Frictional Force along Tool Rake Face and Thrust Force
Go
Created
Cutting Force given Shear Force and Thrust Force
Go
4 More Cutting Force Calculators
Go
Cylinder Properties
(5)
Created
Circulation for Lift Force on Cylinder
Go
Created
Length of Cylinder for Lift Force on Cylinder
Go
Created
Location of Stagnation points for Rotating Cylinder in Uniform Flow Field
Go
Created
Radius of Cylinder for location of Stagnation Points
Go
Created
Radius of Cylinder for Single Stagnation Point
Go
2 More Cylinder Properties Calculators
Go
Cylindrical Blast Wave
(1)
Verified
Simplified Pressure Ratio for Blunt Cylinder Blast Wave
Go
7 More Cylindrical Blast Wave Calculators
Go
Dimensionless Quantities
(2)
Verified
Nusselt's Number with Reynolds Number, Stanton Number and Prandtl Number
Go
Verified
Prandtl Number with Reynolds Number, Nusselt's Number, and Stanton Number
Go
2 More Dimensionless Quantities Calculators
Go
Dimensions and Geometry
(19)
Created
Diameter of Pipe for Difference in Pressure in Viscous Flow
Go
Created
Diameter of Pipe for Head Loss due to Friction in Viscous Flow
Go
Created
Diameter of Pipe for Loss of Pressure Head in Viscous Flow
Go
Created
Diameter of Pipe from Maximum Velocity and Velocity at Any Radius
Go
Created
Diameter of Shaft for Speed and Shear Stress of Fluid in Journal Bearing
Go
Created
Diameter of Shaft for Torque Required in Foot-Step Bearing
Go
Created
Diameter of Sphere in Falling Sphere Resistance Method
Go
Created
External or Outer Radius of Collar for Total Torque
Go
Created
Internal or Inner Radius of Collar for Total Torque
Go
Created
Length for Difference of Pressure in Viscous Flow between Two Parallel Plates
Go
Created
Length for Pressure Head Loss in Viscous Flow between Two Parallel Plates
Go
Created
Length of Pipe for Difference of Pressure in Viscous Flow
Go
Created
Length of Pipe for Head Loss due to Friction in Viscous Flow
Go
Created
Length of Pipe for Loss of Pressure Head in Viscous Flow
Go
Created
Length of Tube in Capillary Tube Method
Go
Created
Radius of Capillary Tube
Go
Created
Thickness of Oil Film for Shear Force in Journal Bearing
Go
Created
Thickness of Oil Film for Speed and Diameter of Shaft in Journal Bearing
Go
Created
Thickness of Oil Film for Torque required in Foot-Step Bearing
Go
Discharge
(17)
Created
Coefficient of Discharge for Time Required to Empty Reservoir
Go
Created
Discharge over Broad-Crested Weir
Go
Created
Discharge over Broad-Crested Weir for Head of Liquid at Middle
Go
Created
Discharge over Broad-Crested Weir with Velocity of Approach
Go
Created
Discharge over Rectangle Notch or Weir
Go
Created
Discharge over Rectangle Weir Considering Bazin's formula
Go
Created
Discharge over Rectangle Weir Considering Francis's formula
Go
Created
Discharge over Rectangle Weir for Bazin's formula with Velocity of Approach
Go
Created
Discharge over Rectangle Weir with Two End Contractions
Go
Created
Discharge over Trapezoidal Notch or Weir
Go
Created
Discharge over Triangular Notch or Weir
Go
Created
Discharge with Velocity of Approach
Go
Created
Discharge without Velocity of Approach
Go
Created
Head of Liquid above V-notch
Go
Created
Head of Liquid at Crest
Go
Created
Time Required to Empty Reservoir
Go
Created
Time Required to Empty Tank with Triangular Weir or Notch
Go
Doublet Flow
(1)
Verified
Stream Function for 2-D Doublet Flow
Go
1 More Doublet Flow Calculators
Go
Downstream Shock Waves
(4)
Verified
Density behind Normal Shock given Upstream Density and Mach Number
Go
Verified
Static Enthalpy behind Normal Shock for given Upstream Enthalpy and Mach Number
Go
Verified
Static Pressure behind Normal Shock for given Upstream Pressure and Mach Number
Go
Verified
Static Temperature behind Normal Shock for given Upstream Temperature and Mach Number
Go
11 More Downstream Shock Waves Calculators
Go
Drag and Forces
(7)
Created
Area of body for Lift Force in body moving on Fluid
Go
Created
Coefficient of drag for sphere in Oseen formula when Reynolds number is between 0.2 and 5
Go
Created
Coefficient of drag for sphere in stoke's law when Reynolds number is less than 0.2
Go
Created
Drag Force for body moving in Fluid of Certain Density
Go
Created
Pressure Drag from Total Drag Force on Sphere
Go
Created
Skin Friction Drag from Total Drag Force on Sphere
Go
Created
Total Drag force on Sphere
Go
4 More Drag and Forces Calculators
Go
Elements of Kinetic Theory
(10)
Verified
Emissivity per Unit Mole
Go
Verified
Kinetic Energy per Mole
Go
Verified
Kinetic Energy per Mole using Molar Volume
Go
Verified
Kinetic Energy per Mole using Temperature of Gas
Go
Verified
Mean Free Path of Single-Species Gas
Go
Verified
Pressure using Kinetic Energy per Mole
Go
Verified
Pressure using Molar Volume
Go
Verified
Specific Gas Constant using Kinetic Energy per Mole
Go
Verified
Temperature of Gas using Emissivity per Unit Mole
Go
Verified
Temperature of Gas using Kinetic Energy per Mole
Go
5 More Elements of Kinetic Theory Calculators
Go
Expansion Waves
(3)
Verified
Forward Mach Angle of Expansion Fan
Go
Verified
Pressure Ratio across Expansion Fan
Go
Verified
Temperature Ratio across Expansion Fan
Go
7 More Expansion Waves Calculators
Go
Flow Analysis
(12)
Created
Difference of Pressure for Viscous Flow between Two Parallel Plates
Go
Created
Difference of Pressure for Viscous or Laminar Flow
Go
Created
Loss of Head Due to Friction
Go
Created
Loss of Pressure Head for Viscous Flow between Two Parallel Plates
Go
Created
Loss of Pressure Head for Viscous Flow through Circular Pipe
Go
Created
Power Absorbed in Collar Bearing
Go
Created
Power Absorbed in Foot-Step Bearing
Go
Created
Power Absorbed in Overcoming Viscous Resistance in Journal Bearing
Go
Created
Viscosity of Fluid or Oil for Capillary Tube Method
Go
Created
Viscosity of Fluid or Oil for Movement of Piston in Dash-Pot
Go
Created
Viscosity of Fluid or Oil in Falling Sphere Resistance Method
Go
Created
Viscosity of Fluid or Oil in Rotating Cylinder Method
Go
1 More Flow Analysis Calculators
Go
Flow Head
(6)
Created
Absolute pressure head at constant head and atmospheric pressure head
Go
Created
Atmospheric pressure head at constant head and absolute pressure head
Go
Created
Head of Liquid above Centre of Orifice
Go
Created
Head of liquid for head loss and coefficient of velocity
Go
Created
Loss of head due to fluid resistance
Go
Created
Loss of head due to sudden enlargement
Go
Flow in Open Channels
(19)
Created
Area of Flow for Circular Channel
Go
Created
Bazin's constant
Go
Created
Chezy's constant considering Bazin formula
Go
Created
Chezy's constant considering Kutter's formula
Go
Created
Chezy's constant considering Manning's formula
Go
Created
Chezy's constant considering velocity
Go
Created
Critical depth considering flow in open channels
Go
Created
Critical depth considering minimum specific energy
Go
Created
Critical Depth using Critical Velocity
Go
Created
Critical velocity considering flow in open channels
Go
Created
Discharge per unit width considering flow in open channels
Go
Created
Hydraulic mean depth considering Bazin formula
Go
Created
Hydraulic mean depth considering Manning's formula
Go
Created
Hydraulic mean depth using Chezy's formula
Go
Created
Manning's coefficient or constant
Go
Created
Minimum Specific Energy using Critical Depth
Go
Created
Radius of Circular Channel using Wetted Perimeter
Go
Created
Velocity of Chezy's formula
Go
Created
Wetted Perimeter for Circular Channel
Go
Flow over Airfoils
(2)
Verified
Boundary Layer Thickness for Laminar Flow
Go
Verified
Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory
Go
6 More Flow over Airfoils Calculators
Go
Flow Rate
(11)
Created
Coefficient of discharge
Go
Created
Coefficient of discharge for area and velocity
Go
Created
Coefficient of Discharge given Time for Emptying Tank
Go
Created
Coefficient of Discharge given Time of Emptying Circular Horizontal Tank
Go
Created
Coefficient of Discharge given Time of Emptying Hemispherical Tank
Go
Created
Discharge in Borda's Mouthpiece Running Free
Go
Created
Discharge in Borda's Mouthpiece Running Full
Go
Created
Discharge in Convergent-Divergent Mouthpiece
Go
Created
Discharge through fully sub-merged orifice
Go
Created
Discharge through large rectangular orifice
Go
Created
Discharge through partially sub-merged orifice
Go
Flow Regime
(14)
Created
Coefficient of contraction for sudden contraction
Go
Created
Discharge in Equivalent Pipe
Go
Created
Retarding force for gradual closure of valves
Go
Created
Time required to close Valve for Gradual Closure of Valves
Go
Created
Time taken by pressure wave to travel
Go
Created
Velocity at Outlet for Head Loss at Exit of Pipe
Go
Created
Velocity at section 1-1 for sudden enlargement
Go
Created
Velocity at section 2-2 for sudden contraction
Go
Created
Velocity at section 2-2 for sudden enlargement
Go
Created
Velocity of Flow at Outlet of Nozzle
Go
Created
Velocity of Flow at outlet of Nozzle for Efficiency and Head
Go
Created
Velocity of Fluid for Head Loss due to Obstruction in Pipe
Go
Created
Velocity of fluid in pipe for head loss at entrance of pipe
Go
Created
Velocity of liquid at vena-contracta
Go
3 More Flow Regime Calculators
Go
Fluid Flow and Resistance
(21)
Created
Angular Speed of Outer Cylinder in Rotating Cylinder Method
Go
Created
Buoyant Force in Falling Sphere Resistance Method
Go
Created
Density of Fluid in Falling Sphere Resistance Method
Go
Created
Discharge in Capillary Tube Method
Go
Created
Drag Force in Falling Sphere Resistance Method
Go
Created
Maximum Velocity at any Radius using Velocity
Go
Created
Rotational Speed considering Power Absorbed and Torque in Journal Bearing
Go
Created
Rotational Speed for Torque Required in Collar Bearing
Go
Created
Rotational Speed for Torque Required in Foot-Step Bearing
Go
Created
Shear Force for Torque and Diameter of Shaft in Journal Bearing
Go
Created
Shear Force or Viscous Resistance in Journal Bearing
Go
Created
Shear Stress in Fluid or Oil of Journal Bearing
Go
Created
Speed of Rotation for Shear Force in Journal Bearing
Go
Created
Torque Required Considering Power Absorbed in Journal Bearing
Go
Created
Torque Required to Overcome Shear Force in Journal Bearing
Go
Created
Torque Required to Overcome Viscous Resistance in Collar Bearing
Go
Created
Torque Required to Overcome Viscous Resistance in Foot-Step Bearing
Go
Created
Total Torque Measured by Strain in Rotating Cylinder Method
Go
Created
Velocity at Any Radius given Radius of Pipe, and Maximum Velocity
Go
Created
Velocity of Piston or Body for Movement of Piston in Dash-Pot
Go
Created
Velocity of Sphere in Falling Sphere Resistance Method
Go
Fluid Parameters and Characteristics
(4)
Created
Freestream Velocity for Lift Coefficient in Rotating Cylinder with Circulation
Go
Created
Freestream velocity for lift coefficient with tangential speed
Go
Created
Freestream Velocity for single Stagnation Point
Go
Created
Tangential velocity for single stagnation point
Go
5 More Fluid Parameters and Characteristics Calculators
Go
Force Along Shear
(2)
Created
Force along shear force for given force normal to shear force, shear, friction and normal rake angle
Go
Created
Force along Shear Force given Cutting Force and Thrust Force
Go
1 More Force Along Shear Calculators
Go
Force Normal to Shear
(1)
Created
Force normal to shear force for given cutting force, thrust force, and shear angle
Go
3 More Force Normal to Shear Calculators
Go
Forces and Friction
(1)
Created
Frictional force along tool rake face for given cutting and thrust forces, normal rake angle
Go
5 More Forces and Friction Calculators
Go
Geometric DImension
(10)
Created
Length of Crest of Weir or Notch
Go
Created
Length of Section for Discharge over Rectangle Notch or Weir
Go
Created
Length of Weir Considering Bazin's formula with Velocity of Approach
Go
Created
Length of Weir Considering Bazin's formula without Velocity of Approach
Go
Created
Length of Weir Considering Francis's formula
Go
Created
Length of Weir for Broad-Crested Weir and Head of Liquid at Middle
Go
Created
Length of Weir for Broad-Crested Weir with Velocity of Approach
Go
Created
Length of Weir for Discharge over Broad-Crested Weir
Go
Created
Length of Weir or Notch for Velocity of Approach
Go
Created
Length of Weir or Notch without Velocity of Approach
Go
Geometric Dimensions
(8)
Created
Area at vena contracta for discharge and constant head
Go
Created
Area of Mouthpiece in Borda's Mouthpiece Running Free
Go
Created
Area of Mouthpiece in Borda's Mouthpiece Running Full
Go
Created
Area of Orifice given Time of Emptying Hemispherical Tank
Go
Created
Area of Tank given Time for Emptying Tank
Go
Created
Coefficient of Contraction given Area of Orifice
Go
Created
Horizontal distance for coefficient of velocity and vertical distance
Go
Created
Vertical distance for coefficient of velocity and horizontal distance
Go
Geometric Property
(7)
Created
Area of Nozzle at Outlet for Maximum Power Transmission through Nozzle
Go
Created
Area of Pipe for Maximum Power Transmission through Nozzle
Go
Created
Diameter of Equivalent Pipe
Go
Created
Diameter of nozzle for maximum power transmission through nozzle
Go
Created
Length of Equivalent Pipe
Go
Created
Length of pipe for maximum power transmission through nozzle
Go
Created
Maximum Area of Obstruction in Pipe
Go
Geometry of Turning Process
(4)
Created
Feed Force
Go
Created
Radial Force
Go
Created
Side Cutting Edge Angle for Orthogonal Cutting
Go
Created
Side Rake Angle for Orthogonal Cutting
Go
6 More Geometry of Turning Process Calculators
Go
Gliding Flight
(1)
Verified
Glide angle for given lift-to-drag ratio
Go
5 More Gliding Flight Calculators
Go
Governing Equations and Sound Wave
(1)
Verified
Ratio of Stagnation and Static Pressure
Go
17 More Governing Equations and Sound Wave Calculators
Go
High Load Factor Maneuver
(5)
Verified
Load factor for given turn radius for high-performance fighter aircraft
Go
Verified
Turn radius for high load factor
Go
Verified
Turn Rate for given Lift Coefficient
Go
Verified
Velocity for given pull-up maneuver rate
Go
Verified
Velocity given Turn Radius for High Load Factor
Go
12 More High Load Factor Maneuver Calculators
Go
Hypersonic Flight Paths Velocity of Altitude Map
(4)
Verified
Pressure Ratio of Blunt-Nosed Cylinder (First Approximation)
Go
Verified
Radial Coordinate of Blunt-Nosed Cylinder (First Approximation)
Go
Verified
Radius for Cylinder-Wedge Body Shape
Go
Verified
Radius for Sphere-Cone Body Shape
Go
5 More Hypersonic Flight Paths Velocity of Altitude Map Calculators
Go
Hypersonic Flow and Disturbances
(6)
Verified
Change in Velocity for Hypersonic Flow in X Direction
Go
Verified
Coefficient of Pressure with Slenderness Ratio and Similarity Constant
Go
Verified
Constant G used for Finding Location of Perturbed Shock
Go
Verified
Density Ratio with Similarity Constant having Slenderness Ratio
Go
Verified
Distance from Tip of Leading Edge to Base
Go
Verified
Non Dimensionalised Time
Go
11 More Hypersonic Flow and Disturbances Calculators
Go
Hypersonic Flow Parameters
(3)
Verified
Mach Ratio at High Mach Number
Go
Verified
Pressure Ratio for High Mach Number
Go
Verified
Pressure Ratio having High Mach Number with Similarity Constant
Go
17 More Hypersonic Flow Parameters Calculators
Go
Hypersonic Flow Parameters
(5)
Verified
Dynamic Viscosity around Wall
Go
Verified
Local Shear Stress at Wall
Go
Verified
Static Density Equation using Skin Friction Coefficient
Go
Verified
Static Velocity Equation using Skin Friction Coefficient
Go
Verified
Static Viscosity Relation using Temperature of Wall
Go
2 More Hypersonic Flow Parameters Calculators
Go
Hypersonic Transition
(13)
Verified
Boundary-Layer Momentum Thickness using Reynolds Number at Transition Point
Go
Verified
Eddy Viscosity Calculation
Go
Verified
Local Mach Number using Reynolds Number Equation at Transition Region
Go
Verified
Location of Transition Point
Go
Verified
Prandtl Number of Transition Flow
Go
Verified
Specific Heat at Constant Pressure for Transient Flow
Go
Verified
Static Density at Transition Point
Go
Verified
Static Density Equation using Boundary-Layer Momentum Thickness
Go
Verified
Static Velocity at Transition Point
Go
Verified
Static Velocity using Boundary-Layer Momentum Thickness
Go
Verified
Static Viscosity at Transition Point
Go
Verified
Static Viscosity Equation using Boundary-Layer Momentum Thickness
Go
Verified
Transition Reynolds Number
Go
3 More Hypersonic Transition Calculators
Go
Incompressible Flow Characteristics
(14)
Created
Dimensions of Rankine half-body
Go
Created
Distance of stagnation point S from source in flow past half body
Go
Created
Location of stagnation point on x-axis
Go
Created
Radial velocity at any radius
Go
Created
Radius at any point considering radial velocity
Go
Created
Radius of Rankine circle
Go
Created
Stream function at point
Go
Created
Stream Function at Point in Combined Flow
Go
Created
Stream function in sink flow for angle
Go
Created
Strength of doublet for stream function
Go
Created
Strength of source for radial velocity and at any radius
Go
Created
Strength of source for Rankine half body
Go
Created
Uniform flow velocity for Rankine half body
Go
Created
Uniform flow velocity for stream function at point in combined flow
Go
9 More Incompressible Flow Characteristics Calculators
Go
Kinematics of Flow
(13)
Created
Actual Discharge in Venturimeter
Go
Created
Angular Velocity of Vortex using Depth of Parabola
Go
Created
Coefficient of pitot-tube for velocity at any point
Go
Created
Depth of Parabola formed at Free Surface of Water
Go
Created
Difference in Pressure Head for heavier Liquid in Manometer
Go
Created
Difference in pressure head for light liquid in manometer
Go
Created
Height or depth of paraboloid for volume of air
Go
Created
Rate of flow or discharge
Go
Created
Resultant bend force along x and y direction
Go
Created
Resultant velocity for two velocity components
Go
Created
Total Pressure Force at Bottom of Cylinder
Go
Created
Total pressure force on top of cylinder
Go
Created
Velocity at any point for coefficient of pitot-tube
Go
4 More Kinematics of Flow Calculators
Go
Kutta-Joukowski Lift Theorem
(2)
Verified
Freestream Density by Kutta-Joukowski Theorem
Go
Verified
Freestream Velocity by Kutta-Joukowski Theorem
Go
2 More Kutta-Joukowski Lift Theorem Calculators
Go
Laminar Boundary Layer at Stagnation point on Blunt body
(5)
Verified
Newtonian Dynamic Pressure
Go
Verified
Newtonian Pressure Distribution over Surface using Cosine Angle
Go
Verified
Nusselt Number at Stagnation Point
Go
Verified
Nusselt Number for Stagnation Point on Blunt Body
Go
Verified
Stagnation Pressure
Go
2 More Laminar Boundary Layer at Stagnation point on Blunt body Calculators
Go
Landing
(1)
Verified
Touchdown velocity
Go
4 More Landing Calculators
Go
Lateral Stability
(5)
Verified
Aircraft forward velocity for given normal component of side velocity
Go
Verified
Aircraft sideslip velocity for given dihedral angle
Go
Verified
Dihedral angle for given sideslip velocity
Go
Verified
Normal component of aircraft side velocity for given dihedral angle
Go
Verified
Normal component of aircraft side velocity for given forward velocity
Go
Lift and Circulation
(15)
Created
Angle of Attack for Circulation developed on Airfoil
Go
Created
Angle of Attack for Lift Coefficient on Airfoil
Go
Created
Chord Length for Circulation developed on Airfoil
Go
Created
Circulation developed on Airfoil
Go
Created
Circulation for Single Stagnation Point
Go
Created
Circulation in Location of Stagnation Points
Go
Created
Coefficient of Lift for Airfoil
Go
Created
Lift coefficient for lift force in body moving on fluid
Go
Created
Lift Coefficient for Rotating Cylinder with Circulation
Go
Created
Lift Coefficient for Rotating Cylinder with Tangential Speed
Go
Created
Lift Force for body moving in Fluid of Certain Density
Go
Created
Lift Force on Cylinder for Circulation
Go
Created
Radius of Cylinder for Lift Coefficient in Rotating Cylinder with Circulation
Go
Created
Tangential Velocity of Cylinder with Lift Coefficient
Go
Created
Velocity of Airfoil for Circulation developed on Airfoil
Go
1 More Lift and Circulation Calculators
Go
Lift and Drag Requirements
(6)
Verified
Coefficient of Lift for given thrust and weight
Go
Verified
Lift Coefficient given Minimum required Thrust
Go
Verified
Lift-to-Drag Ratio given required Thrust of Aircraft
Go
Verified
Total Drag Force given required Power
Go
Verified
Zero-lift drag coefficient at minimum required thrust
Go
Verified
Zero-Lift Drag Coefficient given required Thrust
Go
13 More Lift and Drag Requirements Calculators
Go
Lifting Flow over Cylinder
(2)
Verified
2-D Lift Coefficient for Cylinder
Go
Verified
Stream Function for Lifting Flow over Circular Cylinder
Go
8 More Lifting Flow over Cylinder Calculators
Go
Local Heat Transfer for Hypersonic Flow
(6)
Verified
Local Heat Transfer Rate Calculation using Stanton Number
Go
Verified
Local Heat Transfer Rate using Nusselt's Number
Go
Verified
Stanton Number for Hypersonic Vehicle
Go
Verified
Static Density Equation using Stanton Number
Go
Verified
Static Velocity using Stanton Number
Go
Verified
Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number
Go
3 More Local Heat Transfer for Hypersonic Flow Calculators
Go
Multiphase Compressible Flow
(7)
Created
Absolute Temperature for Velocity of Sound Wave in Isothermal Process
Go
Created
Absolute Temperature for Velocity of Sound Wave using Adiabatic Process
Go
Created
Density of Fluid considering Velocity at Outlet of Orifice
Go
Created
Pressure at Inlet considering Maximum Flow Rate of Fluid
Go
Created
Pressure at Inlet of Tank or Vessel considering Compressible Fluid Flow
Go
Created
Velocity of Sound Wave using Adiabatic Process
Go
Created
Velocity of Sound Wave using Isothermal Process
Go
Newtonian Flow
(5)
Verified
Coefficient of Drag Equation with Coefficient of Normal Force
Go
Verified
Exact Normal Shock Wave Maximum Coefficient of Pressure
Go
Verified
Force Exerted on Surface given Static Pressure
Go
Verified
Mass Flux Incident on Surface Area
Go
Verified
Maximum Pressure Coefficient
Go
9 More Newtonian Flow Calculators
Go
Nonlifting Flow over Cylinder
(1)
Verified
Tangential Velocity for Non-Lifting Flow over Circular Cylinder
Go
9 More Nonlifting Flow over Cylinder Calculators
Go
Oblique Shock
(7)
Verified
Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number
Go
Verified
Density behind Oblique Shock for given Upstream Density and Normal Upstream Mach Number
Go
Verified
Density Ratio across Oblique Shock
Go
Verified
Pressure behind Oblique Shock for given Upstream Pressure and Normal Upstream Mach Number
Go
Verified
Pressure Ratio across Oblique Shock
Go
Verified
Temperature behind Oblique Shock for given Upstream Temperature and Normal Upstream Mach Number
Go
Verified
Temperature Ratio across Oblique Shock
Go
3 More Oblique Shock Calculators
Go
Oblique Shock Relation
(2)
Verified
Parallel Upstream Flow Components after Shock as Mach Tends to Infinite
Go
Verified
Perpendicular Upstream Flow Components behind Shock Wave
Go
13 More Oblique Shock Relation Calculators
Go
Others & Extra
(1)
Verified
Friction Coefficient
Go
8 More Others & Extra Calculators
Go
Planar and Blunt Slab Blast Wave
(3)
Verified
Energy for Blast Wave
Go
Verified
Radial Coordinate of Blunt Slab Blast Wave
Go
Verified
Time Required for Blast Wave
Go
5 More Planar and Blunt Slab Blast Wave Calculators
Go
Power Transmission
(5)
Created
Efficiency of power transmission in flow through pipes
Go
Created
Efficiency of Power Transmission through Nozzle
Go
Created
Efficiency of power transmission through nozzle for velocity and total head
Go
Created
Power Lost ue to Sudden Enlargement
Go
Created
Power transmission through pipes
Go
Preliminary Aerodynamics
(2)
Verified
Power required at Altitude
Go
Verified
Power required at Altitude given Power at sea-level
Go
15 More Preliminary Aerodynamics Calculators
Go
Pressure and Flow Head
(13)
Created
Difference in liquid level in three compound pipes with same friction coefficient
Go
Created
Head available at Base of Nozzle
Go
Created
Head Loss due to Friction for Efficiency of Power Transmission
Go
Created
Intensity of pressure wave produced for gradual closure of valves
Go
Created
Loss of Head at Entrance of Pipe
Go
Created
Loss of head at exit of pipe
Go
Created
Loss of Head due to Bend in Pipe
Go
Created
Loss of Head due to Obstruction in Pipe
Go
Created
Loss of Head due to Sudden Contraction
Go
Created
Loss of head due to sudden enlargement at any particular section of pipe
Go
Created
Loss of head in equivalent pipe
Go
Created
Total head at inlet of pipe for head available at base of nozzle
Go
Created
Total head available at inlet of pipe for efficiency of power transmission
Go
1 More Pressure and Flow Head Calculators
Go
Propeller-Driven Airplane
(11)
Verified
Endurance of Propeller-Driven Airplane
Go
Verified
Power Available for Reciprocating Engine-Propeller Combination
Go
Verified
Propeller Efficiency for given Endurance of Propeller-Driven Airplane
Go
Verified
Propeller Efficiency for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane
Go
Verified
Propeller Efficiency for given Range of Propeller-Driven Airplane
Go
Verified
Propeller Efficiency for Reciprocating Engine-Propeller Combination
Go
Verified
Range of Propeller-Driven Airplane
Go
Verified
Range of Propeller-Driven Airplane for given lift-to-drag ratio
Go
Verified
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
Go
Verified
Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane
Go
Verified
Specific Fuel Consumption for given Range of Propeller-Driven Airplane
Go
11 More Propeller-Driven Airplane Calculators
Go
Property Change Across Shock Waves
(2)
Verified
Static Enthalpy Ratio across Normal Shock
Go
Verified
Temperature Ratio across Normal Shock
Go
4 More Property Change Across Shock Waves Calculators
Go
Pull Up and Pull Down Maneuver
(6)
Verified
Load Factor given Pull-Down Maneuver Radius
Go
Verified
Load Factor given Pull-Up Maneuver Rate
Go
Verified
Pull-down maneuver radius
Go
Verified
Pull-Up Maneuver Rate
Go
Verified
Velocity for given Pull-Down Maneuver Rate
Go
Verified
Velocity for given Pull-Up Maneuver Radius
Go
6 More Pull Up and Pull Down Maneuver Calculators
Go
Reference Temperature Method
(8)
Verified
Chord Length for Flat Plate Case
Go
Verified
Local Reynolds Number
Go
Verified
Mach Number at Reference Temperature
Go
Verified
Overall Skin-Friction Drag Coefficient for Incompressible Flow
Go
Verified
Reference Temperature Equation
Go
Verified
Stanton Number Obtained from Classical Theory
Go
Verified
Static Viscosity of Plate using Chord Length for Flat Plate Case
Go
Verified
Wall Temperature using Reference Temperature
Go
7 More Reference Temperature Method Calculators
Go
Shock Dynamics and Aerodynamic Shape
(7)
Verified
Detachment Distance of Cylinder Wedge Body Shape
Go
Verified
Detachment Distance of Sphere Cone Body Shape
Go
Verified
Grid Point Calculation for Shock Waves
Go
Verified
Nose Radius of Cylinder-Wedge
Go
Verified
Nose Radius of Sphere Cone
Go
Verified
Pressure Ratio for Unsteady Waves
Go
Verified
Ratio of New and Old Temperature
Go
3 More Shock Dynamics and Aerodynamic Shape Calculators
Go
Source Flow
(2)
Verified
Radial Velocity for 2-D Incompressible Source Flow
Go
Verified
Stream Function for Semi-Infinite Body
Go
5 More Source Flow Calculators
Go
Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations
(5)
Verified
Coefficient of Pressure Equation using Specific Heat Ratio
Go
Verified
Curvilinear Grid Location Equation
Go
Verified
Density Equation using Enthalpy and Pressure
Go
Verified
Enthalpy Equation using Pressure and Density
Go
Verified
Pressure Equation using Enthalpy and Density
Go
6 More Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations Calculators
Go
Stagnation Properties
(8)
Created
Density of Fluid for Stagnation considering Compressible Fluid Flow
Go
Created
Stagnation Density considering other Stagnation Properties of Fluid
Go
Created
Stagnation Density given Compressible Fluid Flow
Go
Created
Stagnation Pressure considering other Stagnation Properties of Fluid
Go
Created
Stagnation Pressure for Compressible Fluid Flow
Go
Created
Stagnation Temperature considering Compressible Fluid Flow
Go
Created
Stagnation Temperature considering other Stagnation Properties of Fluid
Go
Created
Temperature of Fluid for Stagnation Temperature considering Compressible Fluid Flow
Go
Static Parameters for Hypersonic Flow
(3)
Verified
Static Density of Fluid over Flat Plate
Go
Verified
Static Temperature over Flat Plate using Static Mach Number
Go
Verified
Static Viscosity using Wall Temperature and Static Temperature
Go
3 More Static Parameters for Hypersonic Flow Calculators
Go
Stick Forces and Hinge Moments
(11)
Verified
Elevator Area given Hinge Moment Coefficient
Go
Verified
Elevator Area given Stick Force
Go
Verified
Elevator Hinge moment coefficient
Go
Verified
Elevator Hinge Moment given Hinge Moment Coefficient
Go
Verified
Flight Velocity for given Stick Force
Go
Verified
Gearing Ratio
Go
Verified
Gearing Ratio given Hinge Moment Coefficient
Go
Verified
Hinge Moment for given Gearing Ratio
Go
Verified
Hinge Moment for given Stick Force
Go
Verified
Stick Deflection Angle for given Stick Force
Go
Verified
Stick Length for given Stick Force
Go
12 More Stick Forces and Hinge Moments Calculators
Go
Supersonic Aerothermodynamics
(5)
Verified
Large Mach Number over Flat Plate using Static Temperature and Wall Temperature
Go
Verified
Pressure Ratio for Cold-Wall Case Strong Interaction
Go
Verified
Pressure Ratio for Cold-Wall Case Weak Interaction
Go
Verified
Viscosity of Wall using Wall Temperature and Static Temperature
Go
Verified
Wall Density of Fluid over Flat Plate
Go
3 More Supersonic Aerothermodynamics Calculators
Go
Tail Contribution
(7)
Verified
Tail Area for given Tail Moment Coefficient
Go
Verified
Tail Efficiency for given Pitching Moment Coefficient
Go
Verified
Tail Lift for given Tail Pitching Moment
Go
Verified
Tail Moment Arm for given Tail Moment Coefficient
Go
Verified
Tail Pitching Moment Coefficient
Go
Verified
Tail Pitching Moment Coefficient for given Tail Efficiency
Go
Verified
Tail Pitching Moment for given Lift Coefficient
Go
12 More Tail Contribution Calculators
Go
Take-Off
(1)
Verified
Liftoff velocity for given weight
Go
14 More Take-Off Calculators
Go
Thermodynamics and Governing Equations
(2)
Verified
Mach Number
Go
Verified
Stagnation Temperature
Go
17 More Thermodynamics and Governing Equations Calculators
Go
Thrust and Power Requirements
(6)
Verified
Minimum Thrust required for given Lift Coefficient
Go
Verified
Power required for given total drag force
Go
Verified
Thrust for given coefficients of lift and drag
Go
Verified
Thrust of aircraft required for given Lift-to-drag ratio
Go
Verified
Weight of Aircraft for given Coefficients of Lift and Drag
Go
Verified
Weight of Aircraft for given Lift-to-Drag Ratio
Go
13 More Thrust and Power Requirements Calculators
Go
Thrust Force
(2)
Created
Thrust force for given cutting force, shear angle and force along shear force
Go
Created
Thrust force for given cutting force, shear angle and force normal to shear force
Go
2 More Thrust Force Calculators
Go
Turbulent Flow
(7)
Created
Average Height of Irregularities for Turbulent Flow in Pipes
Go
Created
Discharge through Pipe given Head Loss in Turbulent Flow
Go
Created
Head Loss due to Friction given Power Required in Turbulent Flow
Go
Created
Power Required to Maintain Turbulent Flow
Go
Created
Roughness Reynold Number for Turbulent Flow in Pipes
Go
Created
Shear Stress Developed for Turbulent Flow in Pipes
Go
Created
Shear Velocity for Turbulent Flow in Pipes
Go
11 More Turbulent Flow Calculators
Go
Uniform Flow
(1)
Verified
Stream Function for Uniform Incompressible Flow
Go
3 More Uniform Flow Calculators
Go
Velocity and Time
(8)
Created
Coefficient of velocity
Go
Created
Coefficient of velocity for horizontal and vertical distance
Go
Created
Coefficient of Velocity given Head Loss
Go
Created
Theoretical velocity
Go
Created
Time of Emptying Circular Horizontal Tank
Go
Created
Time of Emptying Hemispherical Tank
Go
Created
Time of Emptying Tank through Orifice at Bottom
Go
Created
Velocity of liquid at C-C for Hc, Ha, and H
Go
Viscous Flow
(8)
Verified
Aerodynamic Heating Equation for Stanton number
Go
Verified
Coefficient of Friction using Stanton Number for Flat Plate Case
Go
Verified
Drag per Unit Span
Go
Verified
Prandtl Number for Flat Plate with Viscous Flow
Go
Verified
Recovery Factor using Temperature
Go
Verified
Skin-Friction Drag for Flat Plate in Viscous Flow
Go
Verified
Static Density Equation using Aerodynamic Equation
Go
Verified
Static Velocity Equation using Aerodynamic Heating Equation
Go
7 More Viscous Flow Calculators
Go
Vortex Flow
(1)
Verified
Stream Function for 2-D Vortex Flow
Go
2 More Vortex Flow Calculators
Go
Wall Temperature
(1)
Verified
Wall Temperature over Flat Plate using Static Mach Number
Go
3 More Wall Temperature Calculators
Go
Wing-Tail Contribution
(10)
Verified
Angle of incidence of tail
Go
Verified
Lift due to Tail only
Go
Verified
Lift due to Wing only
Go
Verified
Tail area for given tail efficiency
Go
Verified
Tail Efficiency for given lift coefficients
Go
Verified
Tail Lift Coefficient for given Pitching Moment
Go
Verified
Tail Lift Coefficient for given Pitching Moment Coefficient
Go
Verified
Tail Lift Coefficient of Wing-Tail Combination
Go
Verified
Total Lift of Wing-Tail Combination
Go
Verified
Wing Lift Coefficient of wing-tail combination
Go
5 More Wing-Tail Contribution Calculators
Go
Wing-Tail Interaction
(3)
Verified
Wing Area for given Moment Produced by Vertical Tail
Go
Verified
Wing Dynamic Pressure for given Yawing Moment Coefficient
Go
Verified
Wingspan for given Yawing Moment Coefficient
Go
9 More Wing-Tail Interaction Calculators
Go
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