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Diffstat (limited to '3765/CH4/EX4.5/Ex4_5.sce')
| -rw-r--r-- | 3765/CH4/EX4.5/Ex4_5.sce | 31 |
1 files changed, 31 insertions, 0 deletions
diff --git a/3765/CH4/EX4.5/Ex4_5.sce b/3765/CH4/EX4.5/Ex4_5.sce new file mode 100644 index 000000000..98586c4ee --- /dev/null +++ b/3765/CH4/EX4.5/Ex4_5.sce @@ -0,0 +1,31 @@ +clc +// Example 4.5.py +// Consider a 15 deg half angle wedge at zero angle of attack. Calculate the +// pressure coefficient on the wedge surface in a Mach 3 flow of air. + + +// Variable declaration +M1 = 3.0 // upstream mach number +theta = 15.0 // deflection (in degrees) +gamma1 = 1.4 // ratio of specific heats + + +// Calculations +// subscript 2 means behind the shock + +// from figure 4.5 from M1 = 3.0, theta = 15.0 deg. +beta1 = 32.2 // shock angle (in degress) + +// degree to radian conversion is done by multiplying by %pi/180 +// +Mn1 = M1 * sin(beta1*%pi/180) // upstream mach number normal to the shock + +// from Table A2 for Mn1 = 1.6 +p2_by_p1 = 2.82 // p2/p1 + +Cp = 2/(gamma1*M1*M1) * (p2_by_p1 - 1) + + +// Results +printf("\n Coefficient of pressure is %.3f",(Cp)) + |