Temperature Ratios Solution

STEP 0: Pre-Calculation Summary
Formula Used
Temperature Ratio = Pressure Ratio/Density Ratio
Tratio = rp/ρratio
This formula uses 3 Variables
Variables Used
Temperature Ratio - Temperature ratio is the ratio of temperatures at different instances of any process or environment.
Pressure Ratio - Pressure Ratio is ratio of final to initial pressure.
Density Ratio - Density Ratio higher is also one of the definitions of hypersonic flow. Density ratio across normal shock would reach 6 for calorically perfect gas (air or diatomic gas) at very high Mach numbers.
STEP 1: Convert Input(s) to Base Unit
Pressure Ratio: 6 --> No Conversion Required
Density Ratio: 1.65 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Tratio = rpratio --> 6/1.65
Evaluating ... ...
Tratio = 3.63636363636364
STEP 3: Convert Result to Output's Unit
3.63636363636364 --> No Conversion Required
FINAL ANSWER
3.63636363636364 3.636364 <-- Temperature Ratio
(Calculation completed in 00.004 seconds)

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
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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 Ratios Formula

Temperature Ratio = Pressure Ratio/Density Ratio
Tratio = rp/ρratio

What is temperature ratio for hypersonic velocity?

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.

How to Calculate Temperature Ratios?

Temperature Ratios calculator uses Temperature Ratio = Pressure Ratio/Density Ratio to calculate the Temperature Ratio, The Temperature ratios formula is defined as ratio of pressure ratio to density ratio of the hypersonic flow of the fluid before and after shock. Temperature Ratio is denoted by Tratio symbol.

How to calculate Temperature Ratios using this online calculator? To use this online calculator for Temperature Ratios, enter Pressure Ratio (rp) & Density Ratio ratio) and hit the calculate button. Here is how the Temperature Ratios calculation can be explained with given input values -> 3.636364 = 6/1.65.

FAQ

What is Temperature Ratios?
The Temperature ratios formula is defined as ratio of pressure ratio to density ratio of the hypersonic flow of the fluid before and after shock and is represented as Tratio = rpratio or Temperature Ratio = Pressure Ratio/Density Ratio. Pressure Ratio is ratio of final to initial pressure & Density Ratio higher is also one of the definitions of hypersonic flow. Density ratio across normal shock would reach 6 for calorically perfect gas (air or diatomic gas) at very high Mach numbers.
How to calculate Temperature Ratios?
The Temperature ratios formula is defined as ratio of pressure ratio to density ratio of the hypersonic flow of the fluid before and after shock is calculated using Temperature Ratio = Pressure Ratio/Density Ratio. To calculate Temperature Ratios, you need Pressure Ratio (rp) & Density Ratio ratio). With our tool, you need to enter the respective value for Pressure Ratio & Density Ratio 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 Pressure Ratio & Density Ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2
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