initial commit / add all books

1 files changed, 43 insertions, 0 deletions

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))
+