Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle Solution

STEP 0: Pre-Calculation Summary
Formula Used
Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))
Cp = (2*θdef)/(sqrt(Mr^2-1))
This formula uses 1 Functions, 3 Variables
Functions Used
sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)
Variables Used
Pressure Coefficient - Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.
Deflection Angle - (Measured in Radian) - A Deflection angle is the angle between the onward extension of the previous leg and the line ahead.
Mach Number - Mach Number is a dimensionless quantity in fluid dynamics representing the ratio of flow velocity past a boundary to the local speed of sound.
STEP 1: Convert Input(s) to Base Unit
Deflection Angle: 0.19 Radian --> 0.19 Radian No Conversion Required
Mach Number: 1.4 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Cp = (2*θdef)/(sqrt(Mr^2-1)) --> (2*0.19)/(sqrt(1.4^2-1))
Evaluating ... ...
Cp = 0.38783587594067
STEP 3: Convert Result to Output's Unit
0.38783587594067 --> No Conversion Required
FINAL ANSWER
0.38783587594067 0.387836 <-- Pressure Coefficient
(Calculation completed in 00.020 seconds)

Credits

Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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20 Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters
Go Pressure Coefficient = 2*Flow Deflection angle^2*((Specific Heat Ratio+1)/4+sqrt(((Specific Heat Ratio+1)/4)^2+1/Hypersonic Similarity Parameter^2))
Pressure Ratio having High Mach Number with Similarity Constant
Go Pressure Ratio = (1-((Specific Heat Ratio-1)/2)*Hypersonic Similarity Parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
Mach Number with Fluids
Go Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))
Pressure Ratio for High Mach Number
Go Pressure Ratio = (Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
Moment Coefficient
Go Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)
Deflection Angle
Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of shock-1/Mach Number behind shock)
Normal Force Coefficient
Go Coefficient of Force = Normal Force/(Dynamic Pressure*Area for Flow)
Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle
Go Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))
Dynamic Pressure given Coefficient of Lift
Go Dynamic Pressure = Lift Force/(Lift Coefficient*Area for Flow)
Coefficient of Drag
Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area for Flow)
Dynamic Pressure
Go Dynamic Pressure = Drag Force/(Drag Coefficient*Area for Flow)
Lift Coefficient
Go Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)
Axial Force Coefficient
Go Coefficient of Force = Force/(Dynamic Pressure*Area for Flow)
Drag Force
Go Drag Force = Drag Coefficient*Dynamic Pressure*Area for Flow
Lift Force
Go Lift Force = Lift Coefficient*Dynamic Pressure*Area for Flow
Mach Ratio at High Mach Number
Go Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)
Hypersonic Similarity Parameter
Go Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle
Shear-Stress Distribution
Go Shear Stress = Viscosity Coefficient*Velocity Gradient
Fourier's Law of Heat Conduction
Go Heat Flux = Thermal Conductivity*Temperature Gradient
Newtonian Sine Squared Law for Pressure Coefficient
Go Pressure Coefficient = 2*sin(Deflection Angle)^2

Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle Formula

Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))
Cp = (2*θdef)/(sqrt(Mr^2-1))

What is an inviscid fluid?

A nonviscous fluid, that is, a fluid for which all surface forces exerted on the boundaries of each small element of the fluid act normal to these boundaries

How to Calculate Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle?

Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle calculator uses Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1)) to calculate the Pressure Coefficient, The Supersonic expression for pressure coefficient on surface with local deflection angle formula is defined as the ratio of deflection angle to the square root of free-stream Mach number minus 1. Pressure Coefficient is denoted by Cp symbol.

How to calculate Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle using this online calculator? To use this online calculator for Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle, enter Deflection Angle def) & Mach Number (Mr) and hit the calculate button. Here is how the Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle calculation can be explained with given input values -> 0.387836 = (2*0.19)/(sqrt(1.4^2-1)).

FAQ

What is Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle?
The Supersonic expression for pressure coefficient on surface with local deflection angle formula is defined as the ratio of deflection angle to the square root of free-stream Mach number minus 1 and is represented as Cp = (2*θdef)/(sqrt(Mr^2-1)) or Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1)). A Deflection angle is the angle between the onward extension of the previous leg and the line ahead & Mach Number is a dimensionless quantity in fluid dynamics representing the ratio of flow velocity past a boundary to the local speed of sound.
How to calculate Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle?
The Supersonic expression for pressure coefficient on surface with local deflection angle formula is defined as the ratio of deflection angle to the square root of free-stream Mach number minus 1 is calculated using Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1)). To calculate Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle, you need Deflection Angle def) & Mach Number (Mr). With our tool, you need to enter the respective value for Deflection Angle & Mach Number and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Pressure Coefficient?
In this formula, Pressure Coefficient uses Deflection Angle & Mach Number. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Pressure Coefficient = 2*Flow Deflection angle^2*((Specific Heat Ratio+1)/4+sqrt(((Specific Heat Ratio+1)/4)^2+1/Hypersonic Similarity Parameter^2))
  • Pressure Coefficient = 2*sin(Deflection Angle)^2
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