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clc
// Example 5.2.py
// A supersonic wind tunnel is designed to produce Mach 2.5 flow in the test section
// with standard sea level conditions. Calculate the exit area ratio and reservoir
// conditions necessary to achieve these design conditions.
// Variable declaration
Me = 2.5 // exit mach number
pe = 1.0 // sea level pressure (in atm)
Te = 288.0 // sea level temperature (in K)
// Calculations
// from table A1 for Me = 2.5
Ae_by_Astar = 2.637 // Ae/Astar
po_by_pe = 17.09 // po/p
To_by_Te = 2.25 // To/T
po = po_by_pe * pe // reservoir pressure (in atm)
To = To_by_Te * Te // reservoir temperature (in K)
// Results
printf("\n Area ratio required %.3f", Ae_by_Astar)
printf("\n Reservoir pressure required %.2f atm", po)
printf("\n Reservoir temperature required %.1f K", To)
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