Calculate Area at Throat and Exit of Supersonic Wind Tunnel

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• Calculate Continuity Equation for Compressible Flow

• Calculate Bernoulli's Equation

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• Isentropic Flow Calculations

• Calculate Velocity at Throat of Supersonic Wind Tunnel

• Calculate Velocity at Exit of Supersonic Wind Tunnel

• Calculate Area at Throat and Exit of Supersonic Wind Tunnel

• Calculate Local Shear Stress in Laminar Flow Direction

• Calculate Local Shear Stress in Turbulent Flow Direction

• Calculate Airflow Velocity in Test Section of Subsonic Wind Tunnel

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• Calculate Reservoir Pressure for Supersonic Wind Tunnel

• Calculate Temperature Area Ratio for Supersonic Wind Tunnel

• Calculate Pressure at Stagnation Point

• Calculate Temperature at Stagnation Point

• Calculate Density at Stagnation Point

• Calculate Mass Flow through the Nozzle

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• Calculate Mach Number

• Calculate Mach Number of Flow at Nozzle

• Calculate Mach Number of Flow at Exit

• Calculate True Airspeed

• Calculate Calibrated Airspeed

• Calculate Pressure Measured by Pitot Tube

• Calculate Boundary Layer Thickness at Trailing Edge

• Calculate Drag force on Plate

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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.

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