Coefficient of Pressure Derived from Oblique Shock Theory Calculator

✖Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.ⓘ Wave Angle [β]

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✖Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.ⓘ Coefficient of Pressure Derived from Oblique Shock Theory [C_p]

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Coefficient of Pressure Derived from Oblique Shock Theory Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pressure Coefficient = 2*(sin(Wave Angle))^2
C_p = 2*(sin(β))^2
This formula uses 1 Functions, 2 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Pressure Coefficient - Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.
Wave Angle - (Measured in Radian) - Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.

STEP 1: Convert Input(s) to Base Unit

Wave Angle: 0.286 Radian --> 0.286 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_p = 2*(sin(β))^2 --> 2*(sin(0.286))^2

Evaluating ... ...

C_p = 0.159179972017079

STEP 3: Convert Result to Output's Unit

0.159179972017079 --> No Conversion Required

FINAL ANSWER

0.159179972017079 ≈ 0.15918 <-- Pressure Coefficient

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Rushi Shah

K J Somaiya College of Engineering (K J Somaiya), Mumbai

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< Oblique Shock Relation Calculators

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

LaTeX Go Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))

Perpendicular Upstream Flow Components behind Shock Wave

LaTeX Go Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1)

Wave Angle for Small Deflection Angle

LaTeX Go Wave Angle = (Specific Heat Ratio+1)/2*(Deflection Angle*180/pi)*pi/180

Coefficient of Pressure Derived from Oblique Shock Theory

LaTeX Go Pressure Coefficient = 2*(sin(Wave Angle))^2

Coefficient of Pressure Derived from Oblique Shock Theory Formula

LaTeX Go

Pressure Coefficient = 2*(sin(Wave Angle))^2
C_p = 2*(sin(β))^2

What is oblique shock?

An oblique shock wave is a shock wave that, unlike a normal shock, is inclined with respect to the incident upstream flow direction. It will occur when a supersonic flow encounters a corner that effectively turns the flow into itself and compresses

How to Calculate Coefficient of Pressure Derived from Oblique Shock Theory?

Coefficient of Pressure Derived from Oblique Shock Theory calculator uses Pressure Coefficient = 2*(sin(Wave Angle))^2 to calculate the Pressure Coefficient, Coefficient of Pressure Derived from Oblique Shock Theory formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave, providing a crucial parameter in the analysis of supersonic flows and shock waves in aerodynamics and aerospace engineering. Pressure Coefficient is denoted by C_p symbol.

How to calculate Coefficient of Pressure Derived from Oblique Shock Theory using this online calculator? To use this online calculator for Coefficient of Pressure Derived from Oblique Shock Theory, enter Wave Angle (β) and hit the calculate button. Here is how the Coefficient of Pressure Derived from Oblique Shock Theory calculation can be explained with given input values -> 0.15918 = 2*(sin(0.286))^2.

FAQ

What is Coefficient of Pressure Derived from Oblique Shock Theory?

Coefficient of Pressure Derived from Oblique Shock Theory formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave, providing a crucial parameter in the analysis of supersonic flows and shock waves in aerodynamics and aerospace engineering and is represented as C_p = 2*(sin(β))^2 or Pressure Coefficient = 2*(sin(Wave Angle))^2. Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.

How to calculate Coefficient of Pressure Derived from Oblique Shock Theory?

Coefficient of Pressure Derived from Oblique Shock Theory formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave, providing a crucial parameter in the analysis of supersonic flows and shock waves in aerodynamics and aerospace engineering is calculated using Pressure Coefficient = 2*(sin(Wave Angle))^2. To calculate Coefficient of Pressure Derived from Oblique Shock Theory, you need Wave Angle (β). With our tool, you need to enter the respective value for Wave Angle 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 Wave Angle. We can use 3 other way(s) to calculate the same, which is/are as follows -

Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2)
Pressure Coefficient = Change in Static Pressure/Dynamic Pressure
Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2

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