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Diffstat (limited to '3765/CH4/EX4.10/Ex4_10.sce')
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diff --git a/3765/CH4/EX4.10/Ex4_10.sce b/3765/CH4/EX4.10/Ex4_10.sce new file mode 100644 index 000000000..caf6406b9 --- /dev/null +++ b/3765/CH4/EX4.10/Ex4_10.sce @@ -0,0 +1,43 @@ +clc +// Example 4.10.py +// Consider an infinitely this flat plate at 5 degrees angle of attack in a Mach +// 2.6 free stream. Calculate the lift and drag coefficients. + +// + +// Variable declaration +alpha = 5.0 // angle of attack in degrees (in degrees) +M1 = 2.6 // freestream mach number +gamma1 = 1.4 // ratio of specific heats + +// Calculations + +// from table A5 for M1 = 2.6 +v1 = 41.41 // (in degrees) +v2 = v1 + alpha // (in degrees) +// from table A5 for v2 = 46.41 deg +M2 = 2.85 +// from A1 for M1 = 2.6 +po1_by_p1 = 19.95 +// from A1 for M2 = 2.85 +po2_by_p2 = 29.29 + +p2_by_p1 = 1/po2_by_p2 * po1_by_p1 // p2/p1 = p2/po2 * po2/po1 * po1/p1 and po2 = po1 + +// from theta-beta1-M diagram for M1 = 2.6 +theta = 5.0 // deflection (in degrees) +beta1 = 26.5 // shock angle (in degrees) +Mn1 = M1*sin(beta1*%pi/180) // mach number normal to the shock + +// from table A2 for Mn1 = 1.16 +p3_by_p1 = 1.403 // p3/p1 + +cl = 2.0/(gamma1*M1*M1)*(p3_by_p1 - p2_by_p1)*cos(alpha*%pi/180) // coefficient of lift +cd1 = 2.0/(gamma1*M1*M1)*(p3_by_p1 - p2_by_p1)*sin(alpha*%pi/180) // coefficient of drag + + +// Results +printf("\n Lift coefficient : %.3f",(cl)) + +printf("\n Drag coefficient : %.4f",(cd1)) + |