Originally Posted by
englishal
Back to IO's 100kt vertical airflow
Wouldn't the vector sum of the two airflows put the relative airflow at 45° (+ or -) to the wing (tan-1 100/100)? Which if so, and the wings remained attached, would put it above the critical AoA of the wing (and hence stall it?)
cheers
Because the airflow has increased by 41%, the lift at constant AoA will double, but the AOA will move from say 3 to 46, way beyond stall. But interestingly developing say .4 lift Coef vs. the 0.2 at cruise (so lift goes up -Coef Lift is about 20% at Aoa = 3, peaks at say AoA =15 then drops to about 30% at AoA=20 and then goes back up at AoA=40 to about 40% - I had to look that one up and it surprised me). But you are now on an elevator adding power (Wind Vertical Velocity * G * M) so to reduce lift sufficiently to remain level the power output of the wing has to be decreased by a factor of 2.8 (in IO'scase) - which means pitching to an AoA of about 1.
IO's situation in English, the wing would be stalled, stall warner would be going off, but due to the increased airspeed and the fact that the coeficient of lift is high at such an extreme AoA, you are generating bucket loads of lift going up (until the wings fall off)