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
Tratio = (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 - Temperature ratio is the ratio of temperatures at different instances of any process or environment.
Specific Heat Ratio - The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume.
Mach Number - Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
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
Specific Heat Ratio: 1.6 --> No Conversion Required
Mach Number: 8 --> No Conversion Required
Wave Angle: 0.286 Radian --> 0.286 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Tratio = (2*Y*(Y-1))/(Y+1)^2*(M*sin(β))^2 --> (2*1.6*(1.6-1))/(1.6+1)^2*(8*sin(0.286))^2
Evaluating ... ...
Tratio = 1.44674814803688
STEP 3: Convert Result to Output's Unit
1.44674814803688 --> No Conversion Required
FINAL ANSWER
1.44674814803688 1.446748 <-- Temperature Ratio
(Calculation completed in 00.004 seconds)

Credits

Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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K J Somaiya College of Engineering (K J Somaiya), Mumbai
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15 Oblique Shock Relation Calculators

Exact Density Ratio
Go Density Ratio = ((Specific Heat Ratio+1)*(Mach Number*(sin(Wave Angle)))^2)/((Specific Heat Ratio-1)*(Mach Number*(sin(Wave Angle)))^2+2)
Temperature Ratio when Mach Becomes Infinite
Go Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2
Exact Pressure Ratio
Go Pressure Ratio = 1+2*Specific Heat Ratio/(Specific Heat Ratio+1)*((Mach Number*sin(Wave Angle))^2-1)
Pressure Ratio when Mach becomes Infinite
Go Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2
Parallel Upstream Flow Components after Shock as Mach Tends to Infinite
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)
Pressure Coefficient behind Oblique Shock Wave
Go Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2)
Wave Angle for Small Deflection Angle
Go Wave Angle = (Specific Heat Ratio+1)/2*(Deflection Angle*180/pi)*pi/180
Velocity of Sound using Dynamic Pressure and Density
Go Speed of Sound = sqrt((Specific Heat Ratio*Pressure)/Density)
Dynamic Pressure for given Specific Heat Ratio and Mach Number
Go Dynamic Pressure = Specific Heat Ratio Dynamic*Static Pressure*(Mach Number^2)/2
Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number
Go Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2
Non-Dimensional Pressure Coefficient
Go Pressure Coefficient = Change in static pressure/Dynamic Pressure
Density Ratio when Mach Becomes Infinite
Go Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1)
Temperature Ratios
Go Temperature Ratio = Pressure Ratio/Density Ratio
Coefficient of Pressure Derived from Oblique Shock Theory
Go Pressure Coefficient = 2*(sin(Wave Angle))^2

Temperature Ratio when Mach Becomes Infinite Formula

Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2
Tratio = (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, The Temperature ratio when Mach becomes infinite formula is defined as the ratio of Specific heat ratio plus and minus one and multiplied by the Mach number incident at an angle. Temperature Ratio is denoted by Tratio 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 -> 1.449051 = (2*1.6*(1.6-1))/(1.6+1)^2*(8*sin(0.286))^2.

FAQ

What is Temperature Ratio when Mach Becomes Infinite?
The Temperature ratio when Mach becomes infinite formula is defined as the ratio of Specific heat ratio plus and minus one and multiplied by the Mach number incident at an angle and is represented as Tratio = (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 of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume, Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound & Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.
How to calculate Temperature Ratio when Mach Becomes Infinite?
The Temperature ratio when Mach becomes infinite formula is defined as the ratio of Specific heat ratio plus and minus one and multiplied by the Mach number incident at an angle 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
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