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Calculate Area at Throat and Exit of Supersonic Wind Tunnel


Aerospace



How to calculate the Area at Throat and Exit of Supersonic Wind Tunnel In order to calculate the area at throat and exit we consider a supersonic wind tunnel. 

In order to calculate, we would need,
Air temperature in the reservoir of the Wind Tunnel , T0 in Kelvin
Pressure in the reservoir of the Supersonic Wind Tunnel, P0
Static Temperature at the throat of the wind tunnel T* in Kelvin
Static Temperature at the exit of the wind tunnel Te in Kelvin
The mass flow through the nozzle in kg/sec
Cp value for air = 1008 J/kg.K
Performing the calculation and using the energy equation the exit Velocity Ve and the Throat velocity V* are calculated. Now, using the equation of state the density value is computed.
Now, since the nozzle flow is isentropic, we can calculate the density at the throat and the Area at the throat denoted by A*. Furthermore, we can also calculate the density at the exit and the Area at the exit Ae.


Download Free Program to Calculate the Area at Throat and Exit of Supersonic Wind Tunnel

