Consider an airplane with a 1-g stall speed of 66 m/s at 0 m ISA conditions. This stall speed is achieved by deploying slats and flaps. Assume that the suction peak over the slat amounts to C p = −24....

Consider an airplane with a 1-g stall speed of 66 m/s at 0 m ISA conditions. This stall speed is achieved by deploying slats and flaps. Assume that the suction peak over the slat amounts to C_p
= −24.

(a) Calculate the stall Mach number at 0 m ISA conditions.

(b) Calculate the minimum allowed pressure coefficient at 0 m ISA using (7.7).

(c) Calculate the stall speed at 1,655 m and Mach number at 1,655 m altitude.

Assume the lift coefficient and wing loading are the same at both altitudes.

(d) Calculate the minimum allowed pressure coefficient at 1,655 m altitude.

(e) Based on your calculations, do you think the maximum lift coefficient at 1,655 m is still the same as at sea level?