Temperature Ratio when Mach Becomes Infinite Calculator

✖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.ⓘ Specific Heat Ratio [Y]			+10% -10%
✖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.ⓘ Mach Number [M]			+10% -10%
✖The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.ⓘ Wave Angle [β]			+10% -10%

✖The Temperature Ratio is the comparison of temperatures before and after an oblique shock wave, indicating how energy is transformed in hypersonic flow conditions.ⓘ Temperature Ratio when Mach Becomes Infinite [T_ratio]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Hypersonic Flow Formula PDF PDF Image

Temperature Ratio when Mach Becomes Infinite Solution

STEP 0: Pre-Calculation Summary

Formula Used

Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2
T_ratio = (2*Y*(Y-1))/(Y+1)^2*(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

Temperature Ratio - The Temperature Ratio is the comparison of temperatures before and after an oblique shock wave, indicating how energy is transformed in hypersonic flow conditions.
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

T_ratio = (2*Y*(Y-1))/(Y+1)^2*(M*sin(β))^2 --> (2*1.6*(1.6-1))/(1.6+1)^2*(8*sin(0.5))^2

Evaluating ... ...

T_ratio = 4.17808081767182

STEP 3: Convert Result to Output's Unit

4.17808081767182 --> No Conversion Required

FINAL ANSWER

4.17808081767182 ≈ 4.178081 <-- Temperature Ratio

(Calculation completed in 00.004 seconds)

You are here -

Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Oblique Shock Relation » Temperature Ratio when Mach Becomes Infinite

Credits

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

Rushi Shah has verified this Calculator and 200+ more calculators!

< 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

Temperature Ratio when Mach Becomes Infinite Formula

LaTeX Go

Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2
T_ratio = (2*Y*(Y-1))/(Y+1)^2*(M*sin(β))^2

What is temperature ratio when Mach tends to infinity

The ratio of the absolute temperature at the surface of a body (or at a wall Tw) to either the characteristic absolute flow temperature (TΠ) or to the adiabatic wall temperature (Taw)

How to Calculate Temperature Ratio when Mach Becomes Infinite?

Temperature Ratio when Mach Becomes Infinite calculator uses Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2 to calculate the Temperature Ratio, Temperature Ratio when Mach Becomes Infinite formula is defined as a dimensionless quantity that characterizes the temperature change across an oblique shock wave, which occurs when a supersonic flow encounters a sudden change in direction, and is an important parameter in the study of high-speed fluid dynamics and aerospace engineering. Temperature Ratio is denoted by T_ratio symbol.

How to calculate Temperature Ratio when Mach Becomes Infinite using this online calculator? To use this online calculator for Temperature 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 Temperature Ratio when Mach Becomes Infinite calculation can be explained with given input values -> 4.178081 = (2*1.6*(1.6-1))/(1.6+1)^2*(8*sin(0.5))^2.

FAQ

What is Temperature Ratio when Mach Becomes Infinite?

Temperature Ratio when Mach Becomes Infinite formula is defined as a dimensionless quantity that characterizes the temperature change across an oblique shock wave, which occurs when a supersonic flow encounters a sudden change in direction, and is an important parameter in the study of high-speed fluid dynamics and aerospace engineering and is represented as T_ratio = (2*Y*(Y-1))/(Y+1)^2*(M*sin(β))^2 or Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(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 Temperature Ratio when Mach Becomes Infinite?

Temperature Ratio when Mach Becomes Infinite formula is defined as a dimensionless quantity that characterizes the temperature change across an oblique shock wave, which occurs when a supersonic flow encounters a sudden change in direction, and is an important parameter in the study of high-speed fluid dynamics and aerospace engineering is calculated using Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2. To calculate Temperature 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 Temperature Ratio?

In this formula, Temperature 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 -

Temperature Ratio = Pressure Ratio/Density Ratio

Home

FREE PDFs

🔍 Search