Throwing some light on rates of turn

[Crumpp]

Your claim leads to a Cl of 1.47 which is clearly unrealistic and like you fails the sanity check.

Anyhow, CL, CD or Cwhatever values mean absolutely NOTHING if reference surface (and reference length for couple of forces) is unknown. Anybody with basic notions in aerodynamics should know this. I can announce CL values of 1700 for a brick if I just select a reference surface small enough if I wish to do so and nobody could claim me wrong.

The CL values in this report are only interesting in relative terms with respect to different flap angles.

[Crumpp]

The CL values in this report are only interesting in relative terms with respect to different flap angles.

Another interesting fact about basic aerodynamics. Coefficient of lift is independent of altitude and corresponds to an specific angle of attack.

In otherwords, the angle of attack for best turn performance will be the same no matter what the altitude.

Amazing that some simple calculations reflect that basic fact. OHH the INSANITY OF IT ALL!!!

Originally Posted by Crumpp

Another interesting fact about basic aerodynamics. Coefficient of lift is independent of altitude and corresponds to an specific angle of attack.

In otherwords, the angle of attack for best turn performance will be the same no matter what the altitude.

Amazing that some simple calculations reflect that basic fact. OHH the INSANITY OF IT ALL!!!

Mh. IIRC CL does depend on Mach number even at subsonic speeds and thus indirectly on altitude as for the same IAS the Mach number changes with altitude, the speed of sound being intimately linked to temperature.