The formula given in the FLAPS.N section for lift_scalar and drag_scalar is
total_flap_lift = lift_coef_flaps * (system1.lift_scalar * system1.deflectionangleradians + system2.lift_scalar * system 2.deflectionangleradians…)
is this correct, as it looks funny. and if an aircraft has only one flap system as GA aircraft usually do then it’s
total_flap_lift = lift_coef_flaps * (system1.lift_scalar * system1.deflectionangleradians)
Would you not have an overall lift_coef_flaps and then ADD to it the flap lift at each individual flap setting.
What is the difference (using random numbers) between
1 * 3 * 5 = 15
And
0.5 * 6 * 5 = 15
To it’s more logical to add the lift(drag) values per flap setting , not multiply.
I am having issues with flaps in building my aircraft.