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

✖A Deflection angle is the angle between the onward extension of the previous leg and the line ahead.ⓘ Deflection Angle [θ_def]			+10% -10%
✖Mach Number is a dimensionless quantity in fluid dynamics representing the ratio of flow velocity past a boundary to the local speed of sound.ⓘ Mach Number [M_r]			+10% -10%

✖Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.ⓘ Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle [C_p]

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Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle

Formula

`"C"_{"p"} = (2*"θ"_{"def"})/(sqrt("M"_{"r"}^2-1))`

Example

`"0.387836"=(2*"0.19rad")/(sqrt(("1.4")^2-1))`

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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))
C_p = (2*θ_def)/(sqrt(M_r^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

C_p = (2*θ_def)/(sqrt(M_r^2-1)) --> (2*0.19)/(sqrt(1.4^2-1))

Evaluating ... ...

C_p = 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 00.004 seconds)

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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))
C_p = (2*θ_def)/(sqrt(M_r^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 C_p 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 (θ_def) & Mach Number (M_r) 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 C_p = (2*θ_def)/(sqrt(M_r^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 (θ_def) & Mach Number (M_r). 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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