Rushi Shah
K J Somaiya College of Engineering (K J Somaiya), Mumbai
Rushi Shah has created this Calculator and 3+ more calculators!
Alithea Fernandes
Don Bosco College of Engineering (DBCE), Goa
Alithea Fernandes has verified this Calculator and 50+ more calculators!

11 Other formulas that you can solve using the same Inputs

Final Temperature in Adiabatic Process (using pressure)
final temp.=initial temp.*(Final Pressure of System/Initial Pressure of System)^(1-1/(Molar Specific Heat Capacity at Constant Pressure/Molar Specific Heat Capacity at Constant Volume)) GO
Final Temperature in Adiabatic Process (using volume)
final temp.=initial temp.*(Final Volume of System/Initial Volume of System)^(1-Molar Specific Heat Capacity at Constant Pressure/Molar Specific Heat Capacity at Constant Volume) GO
By Pass Factor
by pass factor=(intermediate temperature-final temp.)/ (intermediate temperature-initial temp.) GO
Temperature After a Given Time
Temperature=s temp.+(s temp.-initial temp.)*e^(-temp. constant*Time) GO
Air Resistance Force
Air Resistance=Air Constant*Velocity^2 GO
Archimedes Principle
Archimedes Principle=Density*Acceleration Due To Gravity*Velocity GO
Stokes Force
Stokes Force=6*pi*Radius*Dynamic viscosity*Velocity GO
Centripetal Force
Centripetal Force=(Mass*(Velocity)^2)/Radius GO
Carnot Cycle of Heat Engine
carnot cycle =1-(initial temp./final temp.) GO
Kinetic Energy
Kinetic Energy=(Mass*Velocity^2)/2 GO
Otto Cycle Efficiency
OTE=1-(initial temp./final temp.) GO

Temperature ratio at the start and end of ramming process Formula

Temperature Ratio=1+(((Velocity^2)*(Heat Capacity Ratio-1)))/(2*(Heat Capacity Ratio*[R]*initial temp.))
More formulas
Ram Efficiency GO
Initial mass of evaporant required to be carried for a given flight time GO

What is Ram air?

Ram air refers to the principle of using the airflow created by a moving object to increase ambient pressure. Often, the purpose of a ram air system is to increase an engine's power.

How to Calculate Temperature ratio at the start and end of ramming process ?

Temperature ratio at the start and end of ramming process calculator uses Temperature Ratio=1+(((Velocity^2)*(Heat Capacity Ratio-1)))/(2*(Heat Capacity Ratio*[R]*initial temp.)) to calculate the Temperature Ratio, Temperature ratio at the start and end of ramming process = 1+ (((velocity of aircraft^2) * (adiabatic_index-1))) / (2*(adiabatic_index* [R]* initial_temperature)) Here R is in Joule/Kg-K. Temperature Ratio and is denoted by Tratio symbol.

How to calculate Temperature ratio at the start and end of ramming process using this online calculator? To use this online calculator for Temperature ratio at the start and end of ramming process , enter Velocity (v), initial temp. (T0) and Heat Capacity Ratio (γ) and hit the calculate button. Here is how the Temperature ratio at the start and end of ramming process calculation can be explained with given input values -> 2.948412 = 1+(((60^2)*(10-1)))/(2*(10*[R]*100)).

FAQ

What is Temperature ratio at the start and end of ramming process ?
Temperature ratio at the start and end of ramming process = 1+ (((velocity of aircraft^2) * (adiabatic_index-1))) / (2*(adiabatic_index* [R]* initial_temperature)) Here R is in Joule/Kg-K and is represented as Tratio=1+(((v^2)*(γ-1)))/(2*(γ*[R]*T0)) or Temperature Ratio=1+(((Velocity^2)*(Heat Capacity Ratio-1)))/(2*(Heat Capacity Ratio*[R]*initial temp.)). Velocity, in physics, is a vector quantity (it has both magnitude and direction), and is the time rate of change of position (of an object). , initial temp. is temperature at start of the task and The heat capacity ratio, also known as the adiabatic index, the ratio of specific heats, or Laplace's coefficient, is the ratio of the heat capacity at constant pressure (Cp) to heat capacity at constant volume (Cv). It is sometimes also known as the isentropic expansion factor and is denoted by γ (gamma) for an ideal gas.
How to calculate Temperature ratio at the start and end of ramming process ?
Temperature ratio at the start and end of ramming process = 1+ (((velocity of aircraft^2) * (adiabatic_index-1))) / (2*(adiabatic_index* [R]* initial_temperature)) Here R is in Joule/Kg-K is calculated using Temperature Ratio=1+(((Velocity^2)*(Heat Capacity Ratio-1)))/(2*(Heat Capacity Ratio*[R]*initial temp.)). To calculate Temperature ratio at the start and end of ramming process , you need Velocity (v), initial temp. (T0) and Heat Capacity Ratio (γ). With our tool, you need to enter the respective value for Velocity, initial temp and Heat Capacity Ratio and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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