Item 1065
OTHER: Aerodynamics -
Airfoil - Lift-curve Slope [a]
Notes:
Theory of thin wing sections is 2
π per radial, or 0.110 per degree.Conventional airfoils at low Mach numbers have lift curve slopes of approximately 0.10 per degree or 5.73 per radian.
[Source ~ RWP1 p.12]
Algorithm in MODULE - Airfoil:
For NACA 0012. It is a modified Prandtl-Glauert relationship.
[Source ~ RWP1 p.427 & 428]If (Mach < 0.725) Then
slope_of_lift_curve_DEG = (0.1 / Sqr(1 - (M ^ 2))) - 0.01 * M
Else
slope_of_lift_curve_DEG = 0.677 - 0.744 * M
End If
Other NACA 00xx and 230xx airfoil values have been modified
[Source ~ TWS p.130] from NACA 0012 and put in the above algorithm. To make the value of 0.109 in TWS match the value of 0.10 in RWP1, I am assuming that the values in TWS are based on a higher Mack number of approximately 0.45.No calculations have been done for speeds exceeding M 0.725.
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Last Revised: March 23, 2002