1. An airfoil experiences a minimum pressure coefficient of Cp = −1.0 when flying at M∞ = 0.7, as shown. Calculate: (a) Mach number at the point of Cp, min (b) Cp, max at M ∞ = 0.7 (c) Cp, max at M ∞...

1. An airfoil experiences a minimum pressure coefficient of Cp = −1.0 when flying at M∞ = 0.7, as shown.

Calculate:

(a) Mach number at the point of Cp, min

(b) Cp, max at M_∞
= 0.7

(c) Cp, max at M_∞
= 0

(d) Cp, min at M_∞
= 0

2. The critical pressure coefficient on an airfoil at an angle of attack,α, is C_p, crit = 1.42 in a flow where V_∞
= 200 m/s and T_∞
= 22 ◦C.

Calculate:

(a) the critical Mach number

(b) the incompressible C_p, min

(c) speed of sound at the critical point

(d) the ratio pcrit/p∞

Assume γ = 1.4 and R = 287 J/kg · K.