RE: CONF iture #521
Originally posted by PJ2: for any specific weight there is a direct, corresponding relationship between CAS and AoA regardless of altitude
IMHO that is not exactly true, but maybe good enough for practical purposes below Mmo
regards,
HN39
Example An A330, 205t, cg as QF72, 235 kt CAS:
@ FL 350; M 0.7; AoA = 5.2 deg
FL 200; M 0.52; AoA = 6.1 deg
sealevel, M 0,36; AoA = 6.5 deg
This assumes that the lift coefficient/AoA relation derived from the QF72 maneuver
corrected for Mach-effect per Prandtl-Glauert does not change with Reynolds.