Ok there is a lot of table of speed vs weight vs flaps position
everywhere.
I want to compute them and not use any table. And it obvious that
tables are the result of some computation.
Do you think I can use something like that ?
Vr = sqr( W / (0.5 *
rho(0) * CL0 * S) )
CL0 is CL-0, rho is
You can only estimate it. Aeromatic uses an estimate like this for the CL of
airliners:
0.2 + (4.4 * alpha) + (1.5 * flaps_norm)
if you assume a rotation to 10 degrees for lift-off, then alpha is 0.1748 in
radians, and the above formula becomes:
0.9678 + (1.5 * flaps_norm)
In the case of
