Pressure Ratio when Mach becomes Infinite Solution

STEP 0: Pre-Calculation Summary
Formula Used
Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2
rp = (2*Y)/(Y+1)*(M*sin(β))^2
This formula uses 1 Functions, 4 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 Ratio - The Pressure Ratio is the comparison of pressures before and after an oblique shock wave, indicating changes in fluid dynamics during hypersonic flow.
Specific Heat Ratio - The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows.
Mach Number - The Mach Number is a dimensionless quantity representing the ratio of the speed of an object to the speed of sound in the surrounding medium.
Wave Angle - (Measured in Radian) - The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.
STEP 1: Convert Input(s) to Base Unit
Specific Heat Ratio: 1.6 --> No Conversion Required
Mach Number: 8 --> No Conversion Required
Wave Angle: 0.5 Radian --> 0.5 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
rp = (2*Y)/(Y+1)*(M*sin(β))^2 --> (2*1.6)/(1.6+1)*(8*sin(0.5))^2
Evaluating ... ...
rp = 18.1050168765779
STEP 3: Convert Result to Output's Unit
18.1050168765779 --> No Conversion Required
FINAL ANSWER
18.1050168765779 18.10502 <-- Pressure Ratio
(Calculation completed in 00.004 seconds)

Credits

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Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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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
​ 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

Pressure Ratio when Mach becomes Infinite Formula

​LaTeX ​Go
Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2
rp = (2*Y)/(Y+1)*(M*sin(β))^2

What is pressure ratio of oblique shock relation, when Mach becomes infinite?

Pressure ratio or overall pressure ratio, is the ratio of the stagnation pressure as measured at the front and rear of the body moving in hypersonic flow.

How to Calculate Pressure Ratio when Mach becomes Infinite?

Pressure Ratio when Mach becomes Infinite calculator uses Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2 to calculate the Pressure Ratio, Pressure Ratio when Mach becomes Infinite formula is defined as a measure of the ratio of total pressure behind an oblique shock wave to the total pressure in front of it, used to analyze the behavior of supersonic flows in aerodynamics and aerospace engineering. Pressure Ratio is denoted by rp symbol.

How to calculate Pressure Ratio when Mach becomes Infinite using this online calculator? To use this online calculator for Pressure Ratio when Mach becomes Infinite, enter Specific Heat Ratio (Y), Mach Number (M) & Wave Angle (β) and hit the calculate button. Here is how the Pressure Ratio when Mach becomes Infinite calculation can be explained with given input values -> 18.10502 = (2*1.6)/(1.6+1)*(8*sin(0.5))^2.

FAQ

What is Pressure Ratio when Mach becomes Infinite?
Pressure Ratio when Mach becomes Infinite formula is defined as a measure of the ratio of total pressure behind an oblique shock wave to the total pressure in front of it, used to analyze the behavior of supersonic flows in aerodynamics and aerospace engineering and is represented as rp = (2*Y)/(Y+1)*(M*sin(β))^2 or Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2. The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows, The Mach Number is a dimensionless quantity representing the ratio of the speed of an object to the speed of sound in the surrounding medium & The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.
How to calculate Pressure Ratio when Mach becomes Infinite?
Pressure Ratio when Mach becomes Infinite formula is defined as a measure of the ratio of total pressure behind an oblique shock wave to the total pressure in front of it, used to analyze the behavior of supersonic flows in aerodynamics and aerospace engineering is calculated using Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2. To calculate Pressure Ratio when Mach becomes Infinite, you need Specific Heat Ratio (Y), Mach Number (M) & Wave Angle (β). With our tool, you need to enter the respective value for Specific Heat Ratio, Mach Number & 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 Ratio?
In this formula, Pressure Ratio uses Specific Heat Ratio, Mach Number & Wave Angle. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Pressure Ratio = 1+2*Specific Heat Ratio/(Specific Heat Ratio+1)*((Mach Number*sin(Wave Angle))^2-1)
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