Calculator A to Z
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Chemistry
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Calculators Created by Sanjay Krishna
Sanjay Krishna
Amrita School of Engineering
(ASE)
,
Vallikavu
https://www.linkedin.com/in/sanjay-krishna-80a7b913b/
301
Formulas Created
212
Formulas Verified
75
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 301 and verified 212 calculators across 75 different categories till date.
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
14 More Aerodynamic Nomenclature Calculators
Go
Altitude Effects on Power Required and Available
(1)
Verified
Velocity at an altitude
Go
5 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 the flat under the freestream flow conditions
Go
Created
Drag force over the flat plate
Go
Created
Free stream enthalpy over a flat plate with freestream conditions
Go
Created
Free stream velocity over a flat plate using drag force
Go
Created
Free stream velocity over a flat plate with freestream conditions
Go
Created
Freestream density over flat plate using Stanton number
Go
Created
Freestream density over the flat under the freestream flow conditions
Go
Created
Freestream Stanton number for flat plate
Go
Created
Freestream velocity over flat plate using Stanton number
Go
Created
Insulated flat plate, the strong interaction
Go
Created
Insulated flat plate, the weak interaction
Go
Created
Local heat transfer over flat plate using Stanton number
Go
Created
Total enthalpy over a flat plate with freestream conditions
Go
Created
Wall enthalpy over flat plate using Stanton number
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
Basics
(2)
Verified
Thermal conductance for given thermal resistance
Go
Verified
Total thermal resistance for conduction through two resistances in parallel
Go
3 More Basics Calculators
Go
Basics
(2)
Verified
Mach Angle
Go
Verified
Mayer's formula
Go
5 More Basics Calculators
Go
Blast-wave part 2
(6)
Created
Exact pressure coefficient for blast wave theory
Go
Created
Pressure coefficient combined with blast wave for the shuttle
Go
Created
Pressure coefficient combined with blast wave for the shuttle at angle of attack
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 a string - one hanging free, other lying on a rough horizontal plane
(1)
Verified
Tension in the string
Go
1 More Bodies connected by a string - one hanging free, other lying on a rough horizontal plane Calculators
Go
Bodies connected by a string - one hanging free, other lying on a rough inclined plane
(5)
Verified
Acceleration of the system
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 the string
Go
2 More Bodies connected by a string - one hanging free, other lying on a rough inclined plane Calculators
Go
Bodies connected by a string - one hanging free, other lying on a smooth inclined plane
(3)
Verified
Acceleration of the system
Go
Verified
Angle of inclination for given acceleration
Go
Verified
Angle of inclination for given tension
Go
1 More Bodies connected by a string - one hanging free, other lying on a smooth inclined plane Calculators
Go
Bodies connected by a string and lying on rough inclined planes
(1)
Verified
Frictional force on body A
Go
5 More Bodies connected by a string and lying on rough inclined planes Calculators
Go
Bodies connected by a string and lying on smooth inclined planes
(2)
Verified
Acceleration of the system
Go
Verified
Tension in the string
Go
2 More Bodies connected by a string and lying on smooth inclined planes 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
(11)
Verified
Area of surface for average drag coefficient in boundary layer flows
Go
Verified
Coefficient of drag for Blasius's solution in boundary layer flow
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 the plate for Reynold number in the laminar boundary layer flow
Go
Verified
Reynold number at the end of the plate
Go
Verified
Reynold number for drag coefficient in Blasius's solution of boundary layer flow
Go
Verified
Shear stress at the boundary for turbulent boundary layer over a 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 the laminar boundary layer flow
Go
10 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
Enthalpy of wall using Stanton number
Go
Created
Local heat-transfer rate calculation using Stanton number
Go
Created
local heat-transfer rate using Nusselt's number
Go
Created
local shear stress at the wall
Go
Created
Local skin-friction coefficient
Go
Created
Nusselt number for hypersonic vehicle
Go
Created
Nusselt's number with Reynolds number, the Stanton number and Prandtl number
Go
Created
Prandtl number with Reynolds number, Nusselt's number, Stanton 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 the edge of the boundary layer equation using Nusselt's number
Go
Created
viscosity around the wall
Go
Buoyancy
(3)
Verified
Angle of heel for metacentric height in experimental method
Go
Verified
Meta-centric height in the experimental method
Go
Verified
Movable weight for metacentric height in experimental method
Go
6 More Buoyancy Calculators
Go
Compressible flow
(8)
Verified
Absolute temperature for the velocity of sound wave in the isothermal process
Go
Verified
Absolute temperature for velocity of sound wave in terms of adiabatic process
Go
Verified
Density of fluid considering velocity at outlet of orifice
Go
Verified
Pressure ratio for maximum flow rate through nozzle or orifice
Go
Verified
Stagnation temperature considering the compressible fluid flow
Go
Verified
Temperature of fluid for stagnation temperature considering compressible fluid flow
Go
Verified
Velocity of sound wave in terms of an adiabatic process
Go
Verified
Velocity of sound wave in terms of isothermal process
Go
16 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
Contribution of Aircraft Components (Part 1)
(2)
Verified
Sidewash angle
Go
Verified
Vertical tail moment arm for given lift curve slope
Go
13 More Contribution of Aircraft Components (Part 1) Calculators
Go
Contribution of Aircraft Components (Part 2)
(5)
Verified
Dynamic pressure at vertical tail for given yawing moment coefficient
Go
Verified
Sidewash angle for given yawing moment coefficient
Go
Verified
Vertical tail area for given yawing moment coefficient
Go
Verified
Vertical tail lift curve slope for given yawing moment coefficient
Go
Verified
Yawing moment coefficient for given vertical tail lift curve slope
Go
9 More Contribution of Aircraft Components (Part 2) Calculators
Go
Contribution of Aircraft Components (Part 3)
(4)
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
Verified
Vertical tail volume ratio for given yawing moment coefficient
Go
11 More Contribution of Aircraft Components (Part 3) Calculators
Go
Crystallography
(1)
Created
Atomic Packing Factor
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 a cylindrical wall with convection either side
Go
11 More Cylinders 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
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
2 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 a 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 Hinge Moment
(1)
Verified
Flight velocity for given elevator hinge moment coefficient
Go
4 More Elevator Hinge Moment 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
Flat-Plate for Viscous flow case
(15)
Created
Adiabatic wall enthalpy for flat plate
Go
Created
Adiabatic wall enthalpy using recovery factor
Go
Created
Coefficient of friction using Stanton number for flat plat case
Go
Created
Drag per unit span
Go
Created
Overall skin-friction drag Coefficient
Go
Created
Prandtl number for flat plate 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 for flat plate in viscous flow
Go
Created
Stanton number using aerodynamic heating equation
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 the inviscid flow outside the boundary layer
Go
Flight Envelope
(2)
Verified
Lift Coefficient for a given wing loading and turn radius
Go
Verified
Wing loading for a given turn radius
Go
13 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 considering the 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 considering the critical depth
Go
Verified
Velocity of Chezy's formula
Go
7 More Flow in open channels Calculators
Go
Flow through pipes
(17)
Verified
Coefficient of contraction for sudden contraction
Go
Verified
Difference in liquid level in three compound pipes with same friction coefficient
Go
Verified
Efficiency of power transmission in flow through pipes
Go
Verified
Head available at the base of the nozzle
Go
Verified
Head loss due to friction for the efficiency of power transmission
Go
Verified
Loss of head at the exit of pipe
Go
Verified
Loss of head due to obstruction in a pipe
Go
Verified
Maximum area of obstruction in the pipe
Go
Verified
Power lost due to sudden enlargement
Go
Verified
Power transmission through pipes
Go
Verified
Retarding force for gradual closure of valves
Go
Verified
Time taken by pressure wave to travel
Go
Verified
Total head at the inlet of pipe for head available at the base of the nozzle
Go
Verified
Total head available at inlet of pipe for efficiency of power transmission
Go
Verified
Velocity at the outlet for head loss at the exit of pipe
Go
Verified
Velocity of fluid for head loss due to obstruction in a pipe
Go
Verified
Velocity of liquid at vena-contracta
Go
22 More Flow through pipes Calculators
Go
Forces on sub-merged bodies
(8)
Verified
Circulation for a single stagnation point
Go
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
Verified
Drag force for a body moving in a fluid of certain density
Go
Verified
Freestream velocity for a single stagnation point
Go
Verified
Radius of the cylinder for a single stagnation point
Go
Verified
Tangential velocity for a single stagnation point
Go
Verified
Total drag force on a sphere
Go
23 More Forces on sub-merged bodies Calculators
Go
Fundamentals of Inviscid Incompressible flow
(15)
Verified
Airspeed measurement by Pitot tube for low-speed incompressible flow
Go
Verified
Lift per unit span by Kutta-Joukowski theorem
Go
Verified
Pressure at an upstream point on streamline by Bernoulli's equation
Go
Verified
Pressure Coefficient
Go
Verified
Pressure coefficient in terms of velocity ratio for inncompressible flow
Go
Verified
Radial velocity for non-lifting flow over circular cylinder
Go
Verified
Static pressure in incompressible flow
Go
Verified
Stream function for flow over Rankine oval
Go
Verified
Stream function for uniform incompressible flow in polar coordinates
Go
Verified
Surface pressure coefficient for non-lifting flow over circular cylinder
Go
Verified
Tangential velocity for 2-D Vortex flow
Go
Verified
Tangential velocity for lifting flow over circular cylinder
Go
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
32 More Fundamentals of Inviscid Incompressible flow Calculators
Go
Gliding Flight
(2)
Verified
Lift for given glide angle
Go
Verified
Lift-to-drag ratio for given glide angle
Go
3 More Gliding Flight 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
Energy for the blast wave
Go
Created
formula For creation pressure for the planar blast wave
Go
Created
Modified Energy for the 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 the 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 the 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 the 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 the flight path
Go
Created
Forces acting Perpendicular to the body on the 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 the cylinder-wedge body shape
Go
Created
Radius for the sphere-cone body shape
Go
Created
Radius of curvature for the cylinder-wedge
Go
Created
Radius of curvature for the sphere-cone body shape
Go
Hypersonic Flow
(20)
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 based on coefficient of lift
Go
Created
Fourier’s law of heat conduction
Go
Created
Hypersonic similarity parameter
Go
Created
lift coefficient
Go
Created
Lift Force
Go
Created
Mach number
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 a surface with local deflection angle θ
Go
Hypersonic Inviscid Flowfields: Approximate Methods
(12)
Created
Coefficient of pressure with slenderness ratio
Go
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 the shock formation for expansion wave
Go
Created
Detachment distance of cylinder-wedge
Go
Created
Detachment distance of sphere cone
Go
Created
Grid point calculation for shock waves
Go
Created
Local shock velocity equation
Go
Created
Mach wave behind the shock
Go
Created
Mach wave behind the shock with mach infinity
Go
Created
New pressure after the shock formation for compression wave
Go
Created
New pressure after the 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 the location of perturbed shock
Go
Created
Density ratio with similarity constant having slenderness ratio
Go
Created
Distance from tip of the leading edge to the 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 the shock-wave angle
Go
Created
Similarity constant equation using the 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 the transition point
Go
Created
Prandtl number of the 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 the transition flow
Go
Created
Transition Reynolds number
Go
Hypersonic Viscous Interactions
(18)
Created
Large Mach number over a flat plate using static temperature and wall temperature
Go
Created
Mach number over a flat plate using static temperature and wall temperature
Go
Created
Pressure ratio for cold-wall case the strong interaction
Go
Created
Pressure ratio for cold-wall case the weak interaction
Go
Created
Static density of fluid over the flat plate
Go
Created
Static temperature of fluid over the flat plate
Go
Created
Static temperature of the plate using the wall viscosity
Go
Created
Static temperature over a flat plate under viscous, very high Mach flow
Go
Created
Static temperature over a flat plate using Static Mach Number
Go
Created
Static viscosity using wall temperature and static temperature
Go
Created
Total temperature over a flat plate under viscous Mach flow
Go
Created
Total temperature over a 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 the flat plate
Go
Created
Wall temperature of fluid over the flat plate
Go
Created
Wall temperature of the plate using the wall viscosity
Go
Created
Wall temperature over a flat plate under viscous, very high Mach flow
Go
Created
Wall temperature over a flat plate using Static Mach Number
Go
Ideal flow or Potential flow
(1)
Verified
Radius of the Rankine circle
Go
14 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
Kinematics of flow
(3)
Verified
Height or depth of paraboloid for volume of air
Go
Verified
Total pressure force at the bottom of the cylinder
Go
Verified
Total pressure force on top of the cylinder
Go
4 More Kinematics of flow Calculators
Go
Laminar boundary layer at a stagnation point on a blunt body,
(7)
Created
Dynamic pressure
Go
Created
Newtonian pressure distribution over the surface using cosine angle
Go
Created
Nusselt number at the 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
(2)
Verified
Landing ground roll distance
Go
Verified
Landing ground roll distance using thrust reversal
Go
3 More Landing Performance Calculators
Go
Merchant Force Circle (Mechanics of Orthogonal metal cutting)
(10)
Created
Area of shear plane for given shear angle, width of cut & uncut chip thickness
Go
Created
Coefficient of friction for given forces normal and along the tool rake face
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
Cutting force for given force acting normal to the rake face, thrust force and normal rake angle
Go
Created
Force acting normal to the rake face for given cutting force, thrust force and normal rake angle
Go
Created
Side cutting edge angle for a given width of cut
Go
Created
Thrust force for given force normal to the rake face, cutting force and normal rake angle
Go
Created
Thrust force for given frictional force along tool rake face, cutting force & normal rake angle
Go
Created
Width of cut for given side cutting edge angle
Go
28 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
Go
Modern design-oriented code
(2)
Created
Convective heat transfer to the surface
Go
Created
Radiative heat transfer to the 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 F exerted on the surface
Go
Created
Lift force with angle of attack
Go
Created
Mass flux incident on a surface area
Go
Created
Maximum Pressure coefficient
Go
Created
Modified Newtonian Law
Go
Created
Pressure coefficient for slender 2-D bodies
Go
Created
Pressure coefficient for slender bodies of revolution
Go
Created
Time rate of change of momentum of the mass flux
Go
Normal Shock Waves
(9)
Verified
Characteristic Mach number
Go
Verified
Critical speed of sound from Prandtl relation
Go
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
Mach Number behind the shock
Go
Verified
Prandtl Condition
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
20 More Normal Shock Waves Calculators
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Notches and Weirs
(3)
Verified
Coefficient of discharge for time required to empty a reservoir
Go
Verified
Length of crest of the weir or notch
Go
Verified
Time required to empty a reservoir
Go
24 More Notches and Weirs Calculators
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Oblique Shock and Expansion Waves
(1)
Verified
Component of Upstream Mach normal to oblique shock
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18 More Oblique Shock and Expansion Waves Calculators
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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
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Created
Exact pressure ratio
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Created
Exact relation for pressure coefficient behind an oblique shock wave
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Created
Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite
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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 the shock wave
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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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Orifices and Mouthpieces
(14)
Verified
Area at vena contracta for discharge and constant head
Go
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 considering time of emptying a hemispherical tank
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Verified
Co-efficient of contraction
Go
Verified
Co-efficient of discharge considering time of emptying a hemispherical tank
Go
Verified
Co-efficient of velocity
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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 the convergent-divergent mouthpiece
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Verified
Head of the liquid above the centre of orifice
Go
Verified
Horizontal distance for co-efficient of velocity and vertical distance
Go
Verified
Time of emptying a hemispherical tank
Go
Verified
Vertical distance for co-efficient of velocity and horizontal distance
Go
19 More Orifices and Mouthpieces Calculators
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Plane walls
(2)
Verified
Interface temperature of composite wall of 2 layers when outer surface temperature is known
Go
Verified
Total thermal resistance of a plain wall with convection on either side
Go
20 More Plane walls Calculators
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Power Available and Maximum Velocity
(1)
Verified
Shaft brake power for reciprocating engine-propeller combination
Go
2 More Power Available and Maximum Velocity Calculators
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Power Required for Level Unaccelerated Flight
(3)
Verified
Power required for given aerodynamic coefficients
Go
Verified
Thrust required for given required power
Go
Verified
Weight of aircraft for given required power
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7 More Power Required for Level Unaccelerated Flight Calculators
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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
2 More Range and Endurance of Jet Airplane Calculators
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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
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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
(16)
Created
Chord length for flat plate case
Go
Created
Local Reynolds number
Go
Created
local skin-friction coefficient
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 the Overall skin-friction drag coefficient
Go
Created
Stanton Number obtained from classical theory
Go
Created
Static density of the plate using chord length for flat plate case
Go
Created
Static velocity of the plate using chord length for flat plate case
Go
Created
Static viscosity of the plate using chord length for flat plate case
Go
Created
Turbulent flat-plate skin-friction coefficient
Go
Created
Wall temperature using the reference temperature
Go
Relationship between Stick Force and Hinge Moment
(5)
Verified
Control stick length for given gearing ratio
Go
Verified
Elevator chord length for given stick force
Go
Verified
Elevator deflection angle for given gearing ratio
Go
Verified
Elevator Stick force for given gearing ratio
Go
Verified
Hinge moment coefficient for given stick force
Go
13 More Relationship between Stick Force and Hinge Moment Calculators
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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
Go
Created
total enthalpy equation using specific heat ratio and velocities
Go
Spheres
(2)
Verified
Heat flow rate through a spherical wall
Go
Verified
Thermal resistance of a spherical wall
Go
9 More Spheres Calculators
Go
Tail Contribution
(3)
Verified
Angle of incidence of wing
Go
Verified
Mean aerodynamic chord for given tail pitching moment coefficient
Go
Verified
Vertical tail moment arm for given yawing moment coefficient
Go
18 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
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
Turbulent flow
(2)
Verified
Shear stress developed for turbulent flow in pipes
Go
Verified
Shear velocity for turbulent flow in pipes
Go
5 More Turbulent flow Calculators
Go
Turning Flight
(1)
Verified
Weight during level turn
Go
11 More Turning Flight Calculators
Go
Viscous flow
(16)
Verified
Angular speed of outer cylinder in rotating cylinder method
Go
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
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
Verified
Loss of head due to friction
Go
Verified
Loss of pressure head for viscous flow through circular pipe
Go
Verified
Maximum velocity at any radius with a velocity, and radius of pipe
Go
Verified
Radius of pipe from maximum velocity and velocity at any radius
Go
Verified
Total torque measured by strain in rotating cylinder method
Go
Verified
Velocity at any radius, radius of pipe, and maximum velocity
Go
Verified
Velocity of piston or body for movement of piston in dash-pot
Go
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
36 More Viscous flow Calculators
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Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating
(16)
Created
Aerodynamic heating to the 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 calculator due to internal energy
Go
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