Since the download to this useful Program does not seem to be available and the Author encourages sharing I am posting it here.
I generally set the Wing Incidence to the Airfoils "alpha_s - angle of attack for shockless inflow" as I use the Airfoils "Cl_s - Lift coefficient for shockless inflow" as a control metric in
Profileditor if I am improving the Airfoil or not. A simple repaneling of the Airfoil changes this value. "alpha_s" can be input into Schwerpunkt 52 and corresponds with its calculations.
German Translation below:
Calculate the center of gravity and setting angle difference
0. General
The lift that a model aircraft needs to fly is a direct function of the flight speed and the lift coefficient of the airfoil used, the latter again depending on the attitude angle difference (EWD). It then looks like this:
If the lift is always assumed to be the same, the model needs a larger lift coefficient to fly slowly, which is achieved by a large EWD of, for example, 4°. If I want the model to fly faster, I add depth control or trim lower and thereby reduce the EWD, for example to 0.5°, which means a smaller lift coefficient.
For a specific EWD and the desired flight condition, the model must be balanced, i.e. the center of gravity depends on the EWD. With a large EWD we need a center of gravity further forward than with a small EWD. The position of the overall neutral point of the model depends on the size of the horizontal
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