# CHAPTER11:SUBSONIC COMPRESSIBLE FLOW OVER AIRFOILS LINEAR THEOREY¶

## Example E01 : Pg 382¶

In [1]:
# All the quantities are expressed in SI units
import math
Cp_incompressible = -0.3;                    # Cp for incompressible flow
M = 0.6;                                     # Mach number
# Thus from eq.(11.52)
Cp_compressible = Cp_incompressible/math.sqrt(1-M**2);
print"(a)The Cp after compressibility corrections is:",Cp_compressible,"Cp"

(a)The Cp after compressibility corrections is: -0.375 Cp


## Example E02 : Pg 383¶

In [1]:
# All the quantities are expressed in SI units
import math
cl_incompressible = 2*math.pi;                    # lift curve slope
M_inf = 0.7;                                  # Mach number
# from eq.(11.52)
cl_compressible = cl_incompressible/math.sqrt(1-M_inf**2);        # compressible lift curve slope
print"(a)The cl after compressibility corrections is: cl =",cl_compressible,"alpha"

(a)The cl after compressibility corrections is: cl = 8.7982192499 alpha