DragCoef_AirFoil
Function DragCoef_Airfoil(Re,H\L) returns the drag coefficient for an air foil of infinite length
Inputs
Re - Reynolds number
H\L - ratio of the maximum width of the airfoil to its length
Outputs
DragCoef_AirFoil- drag coefficient [-]
Reference:
Summary of Drag Coefficients of Various Shaped Cylinders,
C.F., D,L, Brown, and R.T. Cliffe,
APEX-299, 12th edition, General Electric, Aircraft Nuclear Propulation Dept., April, 1957
Example:
Re=1e5
H\L=0.10
C_d=DragCoef_AirFoil(Re,H\L)
{Solution:
C_d=0.00678
}