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

✖Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.ⓘ Flow Deflection angle [θ]			+10% -10%
✖Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.ⓘ Mach Number [M]			+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 Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pressure Coefficient = (2*Flow Deflection angle)/(sqrt(Mach Number^2-1))
C_p = (2*θ)/(sqrt(M^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.
Flow Deflection angle - (Measured in Radian) - Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.
Mach Number - Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.

STEP 1: Convert Input(s) to Base Unit

Flow Deflection angle: 0.53 Radian --> 0.53 Radian No Conversion Required
Mach Number: 3.78 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_p = (2*θ)/(sqrt(M^2-1)) --> (2*0.53)/(sqrt(3.78^2-1))

Evaluating ... ...

C_p = 0.290783338900484

STEP 3: Convert Result to Output's Unit

0.290783338900484 --> No Conversion Required

FINAL ANSWER

0.290783338900484 ≈ 0.290783 <-- Pressure Coefficient

(Calculation completed in 00.004 seconds)

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Amrita School of Engineering (ASE), Vallikavu

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< Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

LaTeX 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))

Deflection Angle

LaTeX Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of Shock-1/Mach Number Behind Shock)

Coefficient of Drag

LaTeX Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area For Flow)

Axial Force Coefficient

LaTeX Go Coefficient of Force = Force/(Dynamic Pressure*Area For Flow)

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

Pressure Coefficient = (2*Flow Deflection angle)/(sqrt(Mach Number^2-1))
C_p = (2*θ)/(sqrt(M^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*Flow Deflection angle)/(sqrt(Mach Number^2-1)) to calculate the Pressure Coefficient, Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle formula is defined as a measure of the pressure coefficient on a surface with a local deflection angle in hypersonic flow, which is critical in understanding the aerodynamic characteristics of a body in high-speed flight. 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 Flow Deflection angle (θ) & Mach Number (M) 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 -> 0.290783 = (2*0.53)/(sqrt(3.78^2-1)).

FAQ

What is Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle?

Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle formula is defined as a measure of the pressure coefficient on a surface with a local deflection angle in hypersonic flow, which is critical in understanding the aerodynamic characteristics of a body in high-speed flight and is represented as C_p = (2*θ)/(sqrt(M^2-1)) or Pressure Coefficient = (2*Flow Deflection angle)/(sqrt(Mach Number^2-1)). Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock & Mach number is a dimensionless quantity 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?

Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle formula is defined as a measure of the pressure coefficient on a surface with a local deflection angle in hypersonic flow, which is critical in understanding the aerodynamic characteristics of a body in high-speed flight is calculated using Pressure Coefficient = (2*Flow Deflection angle)/(sqrt(Mach Number^2-1)). To calculate Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle, you need Flow Deflection angle (θ) & Mach Number (M). With our tool, you need to enter the respective value for Flow 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 Flow 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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