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clc
// Example 3.6.py
// Consider a point in a supersonic flow where the static pressure is 0.4 atm. When
// a pitot tube is inserted in the at this point, the pressure measured by the
// pitot tube is 3 atm. Calculate the mach number at this point.
// Variable declaration
p1 = 0.4 // static pressure (in atm)
po2 = 3.0 // pressure measured by the pitot tube (in atm)
//Calculations
// from table A2 for po2/p1 = 7.5
M1 = 2.35
// Results
printf("\n Mach number is %.2f",(M1))
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