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Firstly I want to thank you for your help in my
understanding of the aerodynamic structure of the aircrafts.
I have two questions about the aerodynamics
model
firstly I have a program that calculates lift and
drag versus attack angle coefficients for a given parameterised airfoil and
is it enough for me to modify the config file lift due to alpha
table
Is there any way to calculate thrust and the
engine's effects on the aerodynamics coefficients of Cx, Cy, Cz and
roll pitch and yaw coefficients. Is Cx that the engine produces is approximately
equal to the thrust force that shares the same
vector.
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