Quote:
Originally Posted by FC99
Drag coefficient is wrong.
In level flight drag = thrust.
D=0.5*density*speed^2*drag_coefficient*reference_a rea
From the above equation calculate drag coefficient and use it to calculate drag at different speeds and altitudes. What you called as "drag coefficient" ans used throughout the different examples is not correct.
|
Yes, i just simplified the calculation.
For a certain aircraft, wing area is a constant, my compare/data is on the deck, so air density is also a constant(1.29kg/m^3). Therefore, my "drag coefficient"=real "drag coefficient"*constant. The final result will not be different if you use real drag coefficient in the formular.