Calculator A to Z
🔍
Chemistry
Engineering
Financial
Health
Math
Physics
Playground
Calculators Created by Sanjay Krishna
Sanjay Krishna
Amrita School of Engineering
(ASE)
,
Vallikavu
https://www.linkedin.com/in/sanjay-krishna-80a7b913b/
299
Formulas Created
200
Formulas Verified
110
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 110 different categories till date.
Absolute Temperature
(2)
Verified
Absolute Temperature for Velocity of Sound Wave in Isothermal Process
Go
Verified
Absolute Temperature for Velocity of Sound Wave using Adiabatic Process
Go
Aerodynamic Nomenclature
(4)
Verified
Velocity along roll axis for small sideslip angle
Go
Verified
Velocity along yaw axis for small angle of attack
Go
Verified
Yawing moment
Go
Verified
Yawing moment coefficient
Go
13 More Aerodynamic Nomenclature Calculators
Go
Altitude Effects on Power Required and Available
(1)
Verified
Velocity at Altitude
Go
6 More Altitude Effects on Power Required and Available Calculators
Go
Approximate Results Applied to Hypersonic Vehicles
(15)
Created
Adiabatic wall enthalpy over flat plate using Stanton number
Go
Created
Coefficient of drag over flat under freestream flow conditions
Go
Created
Drag force over flat plate
Go
Created
Free stream enthalpy over flat plate with freestream conditions
Go
Created
Free stream velocity over flat plate using drag force
Go
Created
Free stream velocity over flat plate with freestream conditions
Go
Created
Freestream density over flat plate using Stanton number
Go
Created
Freestream density over flat under freestream flow conditions
Go
Created
Freestream Stanton number for flat plate
Go
Created
Freestream velocity over flat plate using Stanton number
Go
Created
Local heat transfer over flat plate using Stanton number
Go
Created
Pressure ratio for insulated flat plate, strong interaction
Go
Created
Pressure ratio for insulated flat plate, weak interaction
Go
Created
Total enthalpy over flat plate with freestream conditions
Go
Created
Wall enthalpy over flat plate using Stanton number
Go
Basic Aspects, Boundary Layer Results, and Aerodynamic Heating of Viscous Flow
(16)
Created
Aerodynamic heating to surface
Go
Created
Chapman-Rubesin factor
Go
Created
Coefficient of friction using Stanton equation for incompressible flow
Go
Created
Density calculation using Chapman-Rubesin factor
Go
Created
Internal Energy for Hypersonic Flow
Go
Created
Non dimensional internal energy parameter
Go
Created
Non dimensional internal energy parameter using wall-to-freestream temperature ratio
Go
Created
Non dimensional static enthalpy
Go
Created
Stanton equation using Overall skin friction coefficient for incompressible flow
Go
Created
Stanton number for incompressible flow
Go
Created
Static Density calculation using Chapman-Rubesin factor
Go
Created
Static enthalpy
Go
Created
Static viscosity calculation using Chapman-Rubesin factor
Go
Created
Thermal conductivity using Prandtl number
Go
Created
Viscosity calculation using Chapman-Rubesin factor
Go
Created
Wall temperature calculation using internal energy change
Go
Basic Compressible Flow
(2)
Verified
Ratio of Stagnation and Static Density
Go
Verified
Ratio of Stagnation and Static Temperature
Go
4 More Basic Compressible Flow Calculators
Go
Basic Formulas
(6)
Verified
Coefficient of contraction for sudden contraction
Go
Verified
Difference in liquid level in three compound pipes with same friction coefficient
Go
Verified
Maximum Area of Obstruction in Pipe
Go
Verified
Power Lost ue to Sudden Enlargement
Go
Verified
Power transmission through pipes
Go
Verified
Time taken by pressure wave to travel
Go
6 More Basic Formulas Calculators
Go
Basics
(2)
Verified
Mach Angle
Go
Verified
Mayer's formula
Go
6 More Basics Calculators
Go
Basics of HMT
(2)
Verified
Thermal Conductance for given Thermal Resistance
Go
Verified
Total Thermal Resistance for Conduction through Two Resistances in Parallel
Go
3 More Basics of HMT Calculators
Go
Blast-wave part 2
(6)
Created
Pressure coefficient combined with blast wave for shuttle
Go
Created
Pressure coefficient combined with blast wave for shuttle at angle of attack
Go
Created
Pressure coefficient for blast wave theory
Go
Created
Pressure coefficient for blast wave theory at very high values of mach
Go
Created
Pressure coefficient for Blunt-nosed cylinder
Go
Created
Pressure coefficient for Blunt-nosed plate
Go
Bodies connected by string and lying on rough inclined planes
(1)
Verified
Frictional force on body A
Go
5 More Bodies connected by string and lying on rough inclined planes Calculators
Go
Bodies connected by string and lying on smooth inclined planes
(2)
Verified
Acceleration of system with bodies connected by string and lying on smooth inclined planes
Go
Verified
Tension in string if both bodies are lying on smooth inclined planes
Go
2 More Bodies connected by string and lying on smooth inclined planes Calculators
Go
Bodies connected by string, one hanging free, other lying on a rough inclined plane
(5)
Verified
Acceleration of system with bodies one hanging free, other lying on rough inclined plane
Go
Verified
Coefficient of friction for given tension
Go
Verified
Inclination of plane for given frictional force
Go
Verified
Mass of body B for given frictional force
Go
Verified
Tension in string given coefficient of friction of inclined plane
Go
2 More Bodies connected by string, one hanging free, other lying on a rough inclined plane Calculators
Go
Bodies connected by string, one hanging free, other lying on rough horizontal plane
(1)
Verified
Tension in string given coefficient of friction of horizontal plane
Go
1 More Bodies connected by string, one hanging free, other lying on rough horizontal plane Calculators
Go
Bodies connected by string, one hanging free, other lying on smooth inclined plane
(3)
Verified
Acceleration of system with bodies one hanging free and other lying on smooth inclined plane
Go
Verified
Angle of inclination for given acceleration
Go
Verified
Angle of inclination for given tension
Go
1 More Bodies connected by string, one hanging free, other lying on smooth inclined plane Calculators
Go
Body Centered Cubic
(3)
Created
Atomic Radius in BCC
Go
Created
Lattice Constant of BCC
Go
Created
Total volume of atoms in BCC
Go
Boundary Layer Flow
(10)
Verified
Area of surface for average drag coefficient in boundary layer flows
Go
Verified
Distance from leading edge for Blasius's solution in boundary layer flow
Go
Verified
Distance from leading edge in boundary layer flow
Go
Verified
Length of Plate for Reynold number in Laminar Boundary Layer Flow
Go
Verified
Reynold number at end of plate
Go
Verified
Reynold number for drag coefficient in Blasius's solution of boundary layer flow
Go
Verified
Shear Stress at Boundary for Turbulent Boundary Layer over Flat Plate
Go
Verified
Thickness of boundary layer for Blasius's solution in boundary layer flow
Go
Verified
Thickness of boundary layer in boundary layer flow
Go
Verified
Velocity of fluid for Reynold number in Laminar Boundary Layer Flow
Go
11 More Boundary Layer Flow Calculators
Go
Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions
(20)
Created
Adiabatic wall enthalpy using Stanton number
Go
Created
Dynamic viscosity around wall
Go
Created
Enthalpy of wall using Stanton number
Go
Created
Local heat transfer rate using Nusselt's number
Go
Created
Local heat-transfer rate calculation using Stanton number
Go
Created
Local shear stress at wall
Go
Created
Local skin-friction coefficient
Go
Created
Nusselt number for hypersonic vehicle
Go
Created
Nusselt's number with Reynolds number, Stanton number and Prandtl number
Go
Created
Prandtl number with Reynolds number, Nusselt's number, and Stanton number
Go
Created
Reynolds number for given Nusselt's number, Stanton number and Prandtl number
Go
Created
Skin friction coefficient for incompressible flow
Go
Created
Stanton number for hypersonic vehicle
Go
Created
Stanton number with Reynolds number, Nusselt's number, Stanton number and Prandtl number
Go
Created
Static Density equation using skin friction coefficient
Go
Created
Static density equation using Stanton number
Go
Created
Static velocity equation using skin friction coefficient
Go
Created
Static velocity using Stanton number
Go
Created
Static viscosity relation using temperature of wall
Go
Created
Thermal conductivity at edge of boundary layer equation using Nusselt's number
Go
Buoyancy
(3)
Verified
Angle of heel for metacentric height in experimental method
Go
Verified
Meta-centric height in experimental method
Go
Verified
Movable weight for metacentric height in experimental method
Go
8 More Buoyancy Calculators
Go
Circulation
(1)
Verified
Circulation for Single Stagnation Point
Go
3 More Circulation Calculators
Go
Coefficient of Discharge
(1)
Verified
Coefficient of Discharge given Time of Emptying Hemispherical Tank
Go
4 More Coefficient of Discharge Calculators
Go
Coefficient of Velocity
(1)
Verified
Coefficient of velocity
Go
2 More Coefficient of Velocity Calculators
Go
Coefficient's
(2)
Verified
Coefficient of drag for sphere in Oseen formula when Reynolds number is between 0.2 and 5
Go
Verified
Coefficient of drag for sphere in stoke's law when Reynolds number is less than 0.2
Go
3 More Coefficient's Calculators
Go
Compressible Flow
(2)
Verified
Pressure ratio for maximum flow rate through nozzle or orifice
Go
Verified
Temperature of fluid for stagnation temperature considering compressible fluid flow
Go
5 More Compressible Flow Calculators
Go
Computational-Fluid-Dynamic Solutions
(4)
Created
Emissivity
Go
Created
Freestream density
Go
Created
Freestream velocity
Go
Created
Reference viscosity
Go
Conduction
(1)
Created
Fourier's Law of Heat Conduction
Go
5 More Conduction Calculators
Go
Contribution of Aircraft Components- Part 1
(1)
Verified
Sidewash angle
Go
14 More Contribution of Aircraft Components- Part 1 Calculators
Go
Contribution of Aircraft Components- Part 3
(3)
Verified
Dynamic pressure at vertical tail for given vertical tail efficiency
Go
Verified
Dynamic pressure at wing for given vertical tail efficiency
Go
Verified
Vertical tail efficiency
Go
12 More Contribution of Aircraft Components- Part 3 Calculators
Go
Crystallography
(1)
Created
Atomic Packing Factor
Go
Cutting Force
(1)
Created
Cutting Force given Thrust Force and Normal Rake Angle
Go
5 More Cutting Force Calculators
Go
Cylinders
(3)
Verified
Total thermal resistance of 2 cylindrical resistances connected in series.
Go
Verified
Total thermal resistance of 3 cylindrical resistances connected in series
Go
Verified
Total Thermal Resistance of Cylindrical wall with Convection on both Sides
Go
11 More Cylinders Calculators
Go
Diameter of Pipe
(3)
Verified
Diameter of pipe for difference in pressure in viscous flow
Go
Verified
Diameter of pipe for head loss due to friction in viscous flow
Go
Verified
Diameter of pipe for loss of pressure head in viscous flow
Go
1 More Diameter of Pipe Calculators
Go
Discharge
(3)
Verified
Discharge in Borda's Mouthpiece Running Free
Go
Verified
Discharge in Borda's Mouthpiece Running Full
Go
Verified
Discharge in Convergent-Divergent Mouthpiece
Go
3 More Discharge Calculators
Go
Discharge
(1)
Verified
Coefficient of Discharge for Time required to Empty Reservoir
Go
12 More Discharge Calculators
Go
Drag during Level Unaccelerated Flight
(2)
Verified
Coefficient of Drag for given thrust and weight
Go
Verified
Lift-induced drag coefficient for given required thrust
Go
5 More Drag during Level Unaccelerated Flight Calculators
Go
Drag Force on Body
(2)
Verified
Drag Force for body moving in Fluid of Certain Density
Go
Verified
Total Drag force on Sphere
Go
5 More Drag Force on Body Calculators
Go
Dynamics of Fluid Flow
(4)
Verified
Actual discharge in venturimeter
Go
Verified
Difference in pressure head for heavier liquid in manometer
Go
Verified
Difference in pressure head for light liquid in manometer
Go
Verified
Velocity at any point for coefficient of pitot-tube
Go
3 More Dynamics of Fluid Flow Calculators
Go
Elements of Kinetic Theory
(15)
Created
Emissivity per unit mole
Go
Created
Kinetic energy per mole
Go
Created
Kinetic energy per mole using molar volume
Go
Created
Kinetic energy per mole using temperature of gas
Go
Created
Mean free path of single-species gas
Go
Created
Mean free path using number density
Go
Created
Molar volume using kinetic energy per mole
Go
Created
Number density
Go
Created
Pressure of gas using number density
Go
Created
Pressure using kinetic energy per mole
Go
Created
Pressure using molar volume
Go
Created
Specific gas constant using kinetic energy per mole
Go
Created
Temperature of gas using Emissivity per unit mole
Go
Created
Temperature of gas using kinetic energy per mole
Go
Created
Volume of gas
Go
Elevator and Stick Deflection Angles
(1)
Verified
Elevator deflection angle for given gearing ratio
Go
3 More Elevator and Stick Deflection Angles Calculators
Go
Enthalpy and Velocity
(5)
Verified
Enthalpy ahead of normal shock from normal shock energy equation
Go
Verified
Enthalpy behind of normal shock from normal shock energy equation
Go
Verified
Velocity ahead of normal shock by normal shock momentum equation
Go
Verified
Velocity behind of normal shock by normal shock momentum equation
Go
Verified
Velocity upstream of shock using Prandtl relation
Go
6 More Enthalpy and Velocity Calculators
Go
Face Centered Crystal
(3)
Created
Atomic Radius in FCC
Go
Created
Lattice Constant of FCC
Go
Created
Volume of atoms in FCC
Go
Flight Envelope
(2)
Verified
Lift Coefficient for given wing loading and turn radius
Go
Verified
Wing loading for given turn radius
Go
14 More Flight Envelope Calculators
Go
Flow in Open Channels
(12)
Verified
Bazin's constant
Go
Verified
Chezy's constant considering Bazin formula
Go
Verified
Chezy's constant considering velocity
Go
Verified
Critical depth considering flow in open channels
Go
Verified
Critical depth considering minimum specific energy
Go
Verified
Critical Depth using Critical Velocity
Go
Verified
Critical velocity considering flow in open channels
Go
Verified
Discharge per unit width considering flow in open channels
Go
Verified
Hydraulic mean depth considering Bazin formula
Go
Verified
Hydraulic mean depth using Chezy's formula
Go
Verified
Minimum Specific Energy using Critical Depth
Go
Verified
Velocity of Chezy's formula
Go
7 More Flow in Open Channels Calculators
Go
Gearing Ratio
(1)
Verified
Control stick length for given gearing ratio
Go
3 More Gearing Ratio Calculators
Go
Gliding Flight
(2)
Verified
Lift force for given glide angle
Go
Verified
Lift-to-drag ratio for given glide angle
Go
3 More Gliding Flight Calculators
Go
Head Available
(3)
Verified
Head available at Base of Nozzle
Go
Verified
Total head at inlet of pipe for head available at base of nozzle
Go
Verified
Total head available at inlet of pipe for efficiency of power transmission
Go
Hinge Moment
(1)
Verified
Hinge moment coefficient for given stick force
Go
2 More Hinge Moment Calculators
Go
Hypersonic Equivalence Principle and Blast-Wave Theory
(16)
Created
Blunt-nosed flat plate pressure ratio (first approximation)
Go
Created
Boltzmann constant for cylindrical blast wave
Go
Created
Coefficient of drag equation using energy released from blast wave
Go
Created
Creation pressure for planar blast wave
Go
Created
Energy for blast wave
Go
Created
Modified Energy for cylindrical blast wave
Go
Created
Modified pressure equation for cylindrical blast wave
Go
Created
Modified Radial coordinate equation for cylindrical blast wave
Go
Created
Pressure for cylindrical blast wave
Go
Created
Pressure ratio for blunt cylinder blast wave
Go
Created
Pressure ratio for blunt slab blast wave
Go
Created
Radial coordinate for planar blast wave
Go
Created
Radial coordinate of blunt slab blast wave
Go
Created
Radial coordinate of cylindrical blast wave
Go
Created
Simplified pressure ratio for blunt cylinder blast wave
Go
Created
Time required for blast wave
Go
Hypersonic Flight Paths: Velocity-Altitude Map
(9)
Created
Blunt-nosed radial coordinate flat plate (first approximation)
Go
Created
Forces acting on body along flight path
Go
Created
Forces acting Perpendicular to body on flight path
Go
Created
Pressure ratio of Blunt-nosed cylinder (first approximation)
Go
Created
Radial coordinate of Blunt-nosed cylinder (first approximation)
Go
Created
Radius for cylinder-wedge body shape
Go
Created
Radius for sphere-cone body shape
Go
Created
Radius of curvature for cylinder wedge body shape
Go
Created
Radius of curvature for sphere cone body shape
Go
Hypersonic Inviscid Flowfields: Approximate Methods
(11)
Created
Non dimensional radius for hypersonic vehicles
Go
Created
Non-dimensional density
Go
Created
Non-dimensional density for high mach number
Go
Created
Non-dimensional parallel velocity component for high mach number
Go
Created
Non-dimensional perpendicular velocity component for high mach number
Go
Created
Non-dimensional pressure
Go
Created
Non-dimensional pressure for high mach number
Go
Created
Slenderness ratio with cone radius for hypersonic vehicle
Go
Created
Transformed conical variable
Go
Created
Transformed conical variable with cone angle in hypersonic flow
Go
Created
Transformed conical variable with wave angle
Go
Hypersonic Inviscid Flowfields: Exact Methods
(18)
Created
Density before shock formation for compression wave
Go
Created
Density before Shock formation for Expansion Wave
Go
Created
Detachment distance of cylinder wedge body shape
Go
Created
Detachment distance of sphere cone body shape
Go
Created
Grid point calculation for shock waves
Go
Created
Local shock velocity equation
Go
Created
Mach wave behind shock
Go
Created
Mach wave behind shock with mach infinity
Go
Created
New pressure after shock formation for compression wave
Go
Created
New pressure after shock formation, subtracted to velocity for expansion wave
Go
Created
Nose radius of cylinder-wedge
Go
Created
Nose radius of sphere cone
Go
Created
Pressure ratio for unsteady waves
Go
Created
Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves
Go
Created
Ratio of new and old temperature
Go
Created
Ratio of new and old temperature for expansion waves
Go
Created
Temperature ratio for unsteady compression waves
Go
Created
Temperature ratio for unsteady expansion wave
Go
Hypersonic Small-Disturbance Equations
(17)
Created
Change in velocity for hypersonic flow in x direction
Go
Created
Coefficient of pressure with slenderness ratio
Go
Created
Coefficient of pressure with slenderness ratio and similarity constant
Go
Created
Constant g used for finding location of perturbed shock
Go
Created
Density ratio with similarity constant having slenderness ratio
Go
Created
Distance from tip of leading edge to base
Go
Created
Doty and Rasmussen - normal-force coefficient
Go
Created
Inverse of density for hypersonic flow
Go
Created
Inverse of density for hypersonic flow using Mach number
Go
Created
Non dimensional Change in hypersonic disturbance velocity in x direction
Go
Created
Non dimensional Change in hypersonic disturbance velocity in y direction
Go
Created
Non dimensional pressure equation with slenderness ratio
Go
Created
Non dimensional Velocity disturbance in y direction in hypersonic flow
Go
Created
Non- dimensionalised time
Go
Created
Rasmussen closed form expression for shock wave angle
Go
Created
Similarity constant equation using wave angle
Go
Created
Similarity constant equation with slenderness ratio
Go
Hypersonic Transition
(16)
Created
Boundary-layer momentum thickness using Reynolds number at transition point
Go
Created
Eddy viscosity calculation
Go
Created
Local Mach Number using Reynolds number equation at transition region
Go
Created
Location of transition point
Go
Created
Prandtl number of transition flow
Go
Created
Reynolds number equation using boundary-layer momentum thickness
Go
Created
Reynolds number equation using local Mach number
Go
Created
Specific heat at constant pressure for transient flow
Go
Created
Static density at transition point
Go
Created
Static density equation using boundary-layer momentum thickness
Go
Created
Static velocity at transition point
Go
Created
Static velocity using boundary-layer momentum thickness
Go
Created
Static viscosity at transition point
Go
Created
Static viscosity equation using boundary-layer momentum thickness
Go
Created
Thermal conductivity of transition flow
Go
Created
Transition Reynolds number
Go
Hypersonic Viscous Interactions
(18)
Created
Large Mach number over flat plate using static temperature and wall temperature
Go
Created
Mach number over flat plate using static temperature and wall temperature
Go
Created
Pressure Ratio for Cold-Wall case Strong Interaction
Go
Created
Pressure Ratio for Cold-Wall case Weak Interaction
Go
Created
Static density of fluid over flat plate
Go
Created
Static temperature of fluid over flat plate
Go
Created
Static temperature of plate using wall viscosity
Go
Created
Static temperature over flat plate under viscous, very high Mach flow
Go
Created
Static temperature over flat plate using Static Mach Number
Go
Created
Static viscosity using wall temperature and static temperature
Go
Created
Total temperature over flat plate under viscous Mach flow
Go
Created
Total temperature over flat plate under viscous very high Mach flow
Go
Created
viscosity of wall using wall temperature and static temperature
Go
Created
Wall density of fluid over flat plate
Go
Created
Wall Temperature of Fluid over Flat Plate
Go
Created
Wall temperature of plate using wall viscosity
Go
Created
Wall temperature over flat plate under viscous, very high Mach flow
Go
Created
Wall temperature over flat plate using Static Mach Number
Go
Ideal flow or Potential flow
(1)
Verified
Radius of Rankine circle
Go
13 More Ideal flow or Potential flow Calculators
Go
Incompressible flow over airfoil
(4)
Verified
Boundary layer thickness for Turbulent flow
Go
Verified
Center of pressure location for cambered airfoil
Go
Verified
Skin friction drag coefficient for flat plate in laminar flow
Go
Verified
Skin friction drag coefficient for flat plate in Turbulent flow
Go
4 More Incompressible flow over airfoil Calculators
Go
Introduction
(1)
Verified
Diameter of pipe from maximum velocity and velocity at any radius
Go
18 More Introduction Calculators
Go
Introduction
(2)
Verified
Airspeed measurement by Pitot Tube for Low-Speed Incompressible Flow
Go
Verified
Lift per unit Span by Kutta-Joukowski theorem
Go
14 More Introduction Calculators
Go
Kinematics of Flow
(3)
Verified
Height or depth of paraboloid for volume of air
Go
Verified
Total Pressure Force at Bottom of Cylinder
Go
Verified
Total pressure force on top of cylinder
Go
4 More Kinematics of Flow Calculators
Go
Laminar Boundary Layer at Stagnation point on Blunt body
(7)
Created
Newtonian Dynamic pressure
Go
Created
Newtonian Pressure distribution over Surface using Cosine Angle
Go
Created
Nusselt number at stagnation point
Go
Created
Nusselt number for stagnation point on blunt body
Go
Created
Reynolds analogy factor in Finite deference method
Go
Created
Reynolds analogy for Stanton number in finite difference method
Go
Created
Stagnation pressure
Go
Landing Performance
(1)
Verified
Landing ground roll distance
Go
3 More Landing Performance Calculators
Go
Length of Pipe
(3)
Verified
Length of pipe for difference of pressure in viscous flow
Go
Verified
Length of pipe for head loss due to friction in viscous flow
Go
Verified
Length of pipe for loss of pressure head in viscous flow
Go
Longitudinal Control of Elevator Hinge Moment
(1)
Verified
Flight velocity for given elevator hinge moment coefficient
Go
4 More Longitudinal Control of Elevator Hinge Moment Calculators
Go
Loss of Head
(2)
Verified
Loss of head due to friction
Go
Verified
Loss of pressure head for viscous flow through circular pipe
Go
1 More Loss of Head Calculators
Go
Loss of Head
(3)
Verified
Head Loss due to Friction for Efficiency of Power Transmission
Go
Verified
Loss of head at exit of pipe
Go
Verified
Loss of head due to obstruction in pipe
Go
5 More Loss of Head Calculators
Go
Merchant Force Circle (Mechanics of Orthogonal metal cutting)
(7)
Created
Area of shear plane for given shear angle, width of cut and uncut chip thickness
Go
Created
Coefficient of friction for given friction angle
Go
Created
Coefficient of friction for given thrust force, cutting force and normal rake angle
Go
Created
Coefficient of Friction given Forces Normal and along Tool Rake Face
Go
Created
Force acting Normal to Rake Face given Cutting Force and Thrust Force
Go
Created
Side cutting edge angle for given width of cut
Go
Created
Width of cut for given side cutting edge angle
Go
15 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
Go
Modern design-oriented code
(2)
Created
Convective heat transfer to surface
Go
Created
Radiative heat transfer to surface stemming from thermal radiation
Go
Newtonian Flow
(14)
Created
Coefficient of drag equation with angle of attack
Go
Created
Coefficient of drag equation with coefficient of normal force
Go
Created
Coefficient of lift equation with angle of attack
Go
Created
Coefficient of lift equation with coefficient of normal force
Go
Created
Drag force with angle of attack
Go
Created
Exact normal shock wave maximum coefficient of pressure
Go
Created
Force Exerted on Surface given Static Pressure
Go
Created
Lift force with angle of attack
Go
Created
Mass Flux Incident on Surface Area
Go
Created
Maximum Pressure coefficient
Go
Created
Modified Newtonian Law
Go
Created
Pressure coefficient for slender 2D bodies
Go
Created
Pressure coefficient for slender bodies of revolution
Go
Created
Time rate of change of momentum of mass flux
Go
Normal Shock Waves
(4)
Verified
Characteristic Mach number
Go
Verified
Critical speed of sound from Prandtl relation
Go
Verified
Mach Number behind Shock
Go
Verified
Prandtl Condition
Go
16 More Normal Shock Waves Calculators
Go
Notches and Weirs
(2)
Verified
Length of Crest of Weir or Notch
Go
Verified
Time required to Empty Reservoir
Go
4 More Notches and Weirs Calculators
Go
Oblique Shock and Expansion Waves
(1)
Verified
Component of Upstream Mach normal to oblique shock
Go
18 More Oblique Shock and Expansion Waves Calculators
Go
Oblique Shock Relation
(15)
Created
Coefficient of pressure derived from oblique shock theory
Go
Created
Density ratio when Mach become infinite
Go
Verified
Dynamic pressure for given specific heat ratio and Mach number
Go
Created
Exact Density Ratio
Go
Created
Exact pressure ratio
Go
Created
Non-dimensional pressure coefficient
Go
Created
Parallel upstream flow components after shock as Mach tends to infinite
Go
Created
Perpendicular Upstream Flow Components behind Shock Wave
Go
Created
Pressure Coefficient behind Oblique Shock Wave
Go
Created
Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number
Go
Created
Pressure ratio when Mach becomes infinite
Go
Created
Temperature ratio when Mach becomes infinite
Go
Created
Temperature ratios
Go
Created
Velocity of sound using dynamic pressure and density
Go
Created
Wave angle for small deflection angle
Go
Orifices and Mouthpieces
(8)
Verified
Area at vena contracta for discharge and constant head
Go
Verified
Area of Mouthpiece in Borda's Mouthpiece Running Free
Go
Verified
Area of Mouthpiece in Borda's Mouthpiece Running Full
Go
Verified
Area of Orifice given Time of Emptying Hemispherical Tank
Go
Verified
Coefficient of Contraction given Area of Orifice
Go
Verified
Head of Liquid above Centre of Orifice
Go
Verified
Horizontal distance for coefficient of velocity and vertical distance
Go
Verified
Vertical distance for coefficient of velocity and horizontal distance
Go
8 More Orifices and Mouthpieces Calculators
Go
Parameters
(19)
Created
Axial force coefficient
Go
Created
Coefficient of drag
Go
Created
Coefficient of pressure with similarity parameters
Go
Created
Deflection angle
Go
Created
Drag force
Go
Created
Dynamic pressure
Go
Created
Dynamic Pressure given Coefficient of Lift
Go
Created
Hypersonic similarity parameter
Go
Created
Lift coefficient
Go
Created
Lift Force
Go
Created
Mach number with fluids
Go
Created
Mach ratio at high mach number
Go
Created
Moment coefficient
Go
Created
Newtonian sine squared law for pressure coefficient
Go
Created
Normal Force Coefficient
Go
Created
Pressure ratio for high Mach number
Go
Created
Pressure ratio having high mach number with similarity constant
Go
Created
Shear-stress distribution.
Go
Created
Supersonic expression for pressure coefficient on surface with local deflection angle
Go
1 More Parameters Calculators
Go
Plane Walls
(2)
Verified
Interface temperature of composite wall of 2 layers given outer surface temperature
Go
Verified
Total Thermal Resistance of Plane Wall with Convection on both Sides
Go
20 More Plane Walls Calculators
Go
Power Available and Maximum Velocity
(1)
Verified
Shaft brake power for reciprocating engine-propeller combination
Go
2 More Power Available and Maximum Velocity Calculators
Go
Power Required for Level Unaccelerated Flight
(3)
Verified
Power required for given aerodynamic coefficients
Go
Verified
Thrust of aircraft required for given required power
Go
Verified
Weight of aircraft for given required power
Go
7 More Power Required for Level Unaccelerated Flight Calculators
Go
Power Transmission Efficiency
(1)
Verified
Efficiency of power transmission in flow through pipes
Go
2 More Power Transmission Efficiency Calculators
Go
Pressure
(4)
Verified
Pressure at upstream point on streamline by Bernoulli's equation
Go
Verified
Pressure Coefficient
Go
Verified
Static pressure in incompressible flow
Go
Verified
Surface pressure coefficient for non-lifting flow over circular cylinder
Go
9 More Pressure Calculators
Go
Pressure and Density
(1)
Verified
Density of fluid considering velocity at outlet of orifice
Go
3 More Pressure and Density Calculators
Go
Radial Velocity
(1)
Verified
Radial velocity for non-lifting flow over circular cylinder
Go
2 More Radial Velocity Calculators
Go
Range and Endurance of Jet Airplane
(5)
Verified
Endurance for given Lift-to-Drag ratio of Jet Airplane
Go
Verified
Lift-to-Drag ratio for given Endurance of Jet Airplane
Go
Verified
Range of Jet Airplane
Go
Verified
Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
Go
Verified
Thrust-Specific Fuel Consumption for given Range of Jet Airplane
Go
3 More Range and Endurance of Jet Airplane Calculators
Go
Range and Endurance of Propeller-Driven Airplane
(1)
Verified
Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
Go
9 More Range and Endurance of Propeller-Driven Airplane Calculators
Go
Rate of Climb
(3)
Verified
Rate of Climb
Go
Verified
Rate of Climb for given excess power
Go
Verified
Weight of aircraft for given excess power
Go
7 More Rate of Climb Calculators
Go
Reference Temperature Method
(15)
Created
Chord length for flat plate case
Go
Created
Local Reynolds number
Go
Created
Local turbulent skin-friction coefficient for incompressible flow
Go
Created
Mach number at reference temperature
Go
Created
Overall skin-friction drag coefficient
Go
Created
Overall skin-friction drag coefficient for incompressible flow
Go
Created
Reference temperature equation
Go
Created
Reynolds number for chord length
Go
Created
Reynolds number for chord length using Overall skin-friction drag coefficient
Go
Created
Stanton Number obtained from classical theory
Go
Created
Static density of plate using chord length for flat plate case
Go
Created
Static velocity of plate using chord length for flat plate case
Go
Created
Static viscosity of plate using chord length for flat plate case
Go
Created
Turbulent flat-plate skin-friction coefficient
Go
Created
Wall temperature using reference temperature
Go
Simple Cubic Cell
(3)
Created
Atomic Radius in SCC
Go
Created
Lattice Constant of SCC
Go
Created
Total volume of atoms in SCC
Go
Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations
(11)
Created
Coefficient of pressure equation using specific heat ratio
Go
Created
curvilinear grid location equation
Go
Created
Density equation using enthalpy and pressure
Go
Created
Enthalpy equation using coefficient of pressure for calorically perfect gas
Go
Created
Enthalpy equation using pressure and density
Go
Created
Enthalpy equation using specific heat ratio
Go
Created
Free stream enthalpy
Go
Created
local shock-layer thickness
Go
Created
pressure equation using Enthalpy and density
Go
Created
total enthalpy equation using specific heat ratio and velocities
Go
Created
Total specific enthalpy
Go
Spheres
(2)
Verified
Heat flow rate through spherical wall
Go
Verified
Thermal Resistance of Spherical Wall
Go
9 More Spheres Calculators
Go
Stagnation Points
(1)
Verified
Radius of Cylinder for Single Stagnation Point
Go
3 More Stagnation Points Calculators
Go
Stagnation Temperature
(1)
Verified
Stagnation Temperature considering Compressible Fluid Flow
Go
1 More Stagnation Temperature Calculators
Go
Stick Forces
(2)
Verified
Elevator chord length for given stick force
Go
Verified
Elevator Stick force for given gearing ratio
Go
5 More Stick Forces Calculators
Go
Stream Function
(2)
Verified
Stream function for flow over Rankine oval
Go
Verified
Stream function for uniform incompressible flow in polar coordinates
Go
7 More Stream Function Calculators
Go
Tail Contribution
(2)
Verified
Angle of incidence of wing
Go
Verified
Mean aerodynamic chord for given tail pitching moment coefficient
Go
19 More Tail Contribution Calculators
Go
Tail Contribution Contd
(4)
Verified
Horizontal tail volume ratio for given pitching moment coefficient
Go
Verified
Tail Efficiency for given tail volume ratio
Go
Verified
Tail lift coefficient for given tail volume ratio
Go
Verified
Tail Pitching moment coefficient for given tail volume ratio
Go
10 More Tail Contribution Contd Calculators
Go
Takeoff Performance
(1)
Verified
Liftoff velocity for given stall velocity
Go
13 More Takeoff Performance Calculators
Go
Tangential Velocity
(2)
Verified
Tangential velocity for 2-D Vortex flow
Go
Verified
Tangential velocity for lifting flow over circular cylinder
Go
1 More Tangential Velocity Calculators
Go
Thrust Force
(2)
Created
Thrust force for given frictional force along tool rake face, cutting force and normal rake angle
Go
Created
Thrust Force given Cutting Force and Normal Rake Angle
Go
2 More Thrust Force Calculators
Go
Thrust Required for Level Unaccelerated Flight
(2)
Verified
Minimum Thrust required for given weight
Go
Verified
Thrust-to-weight ratio
Go
10 More Thrust Required for Level Unaccelerated Flight Calculators
Go
Time of Emptying
(1)
Verified
Time of Emptying Hemispherical Tank
Go
2 More Time of Emptying Calculators
Go
Torque Required
(1)
Verified
Total torque measured by strain in rotating cylinder method
Go
4 More Torque Required Calculators
Go
Turbulent Flow
(2)
Verified
Shear stress developed for turbulent flow in pipes
Go
Verified
Shear velocity for turbulent flow in pipes
Go
16 More Turbulent Flow Calculators
Go
Turning Flight
(1)
Verified
Weight of aircraft during level turn
Go
11 More Turning Flight Calculators
Go
Valves
(1)
Verified
Retarding force for gradual closure of valves
Go
3 More Valves Calculators
Go
Velocity
(4)
Verified
Angular speed of outer cylinder in rotating cylinder method
Go
Verified
Maximum velocity at any Radius using Velocity
Go
Verified
Velocity at any radius given radius of pipe, and maximum velocity
Go
Verified
Velocity of piston or body for movement of piston in dash-pot
Go
1 More Velocity Calculators
Go
Velocity
(2)
Verified
Freestream Velocity for single Stagnation Point
Go
Verified
Tangential velocity for single stagnation point
Go
4 More Velocity Calculators
Go
Velocity of Flow
(3)
Verified
Velocity at Outlet for Head Loss at Exit of Pipe
Go
Verified
Velocity of Fluid for Head Loss due to Obstruction in Pipe
Go
Verified
Velocity of liquid at vena-contracta
Go
6 More Velocity of Flow Calculators
Go
Velocity of Sound Wave
(2)
Verified
Velocity of Sound Wave using Adiabatic Process
Go
Verified
Velocity of Sound Wave using Isothermal Process
Go
4 More Velocity of Sound Wave Calculators
Go
Velocity Potential
(3)
Verified
Velocity potential for 2-D doublet flow
Go
Verified
Velocity potential for 2-D source flow
Go
Verified
Velocity potential for uniform incompressible flow in polar coordinates
Go
2 More Velocity Potential Calculators
Go
Viscosity of Fluid
(2)
Verified
Viscosity of fluid or oil for movement of piston in dash-pot
Go
Verified
Viscosity of fluid or oil in rotating cylinder method
Go
3 More Viscosity of Fluid Calculators
Go
Viscous Flow
(15)
Created
Adiabatic wall enthalpy for flat plate
Go
Created
Adiabatic wall enthalpy using recovery factor
Go
Created
Aerodynamic Heating Equation for Stanton number
Go
Created
Coefficient of friction using Stanton number for flat plat case
Go
Created
Drag per unit span
Go
Created
Prandtl number for flat plate with viscous flow
Go
Created
Recovery factor calculation using Prandtl number
Go
Created
Recovery factor for flat plate with viscous flow
Go
Created
Recovery Factor using temperature
Go
Created
Skin-friction drag Coefficient
Go
Created
Skin-friction drag for flat plate in viscous flow
Go
Created
Stanton number with coefficient of friction
Go
Created
Static density equation using aerodynamic equation
Go
Created
Static velocity equation using aerodynamic heating equation
Go
Created
Total enthalpy in inviscid flow outside boundary layer
Go
Share
Facebook
Twitter
WhatsApp
Reddit
LinkedIn
E-Mail
Let Others Know
✖
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!