Repeat Problem 17.30 if the angle of attack is the stall point, 19.6°.Problem 17.30For the...

Repeat Problem 17.30 if the angle of attack is the stall point, 19.6°.

Problem 17.30

For the airfoil with the performance characteristics shown in Fig. 17.11, determine the lift and drag at an angle of attack of 10°. The airfoil has a chord length of 1.4 m and a span of 6.8 m. Perform the calculation at a speed of 200 km/h in the standard atmosphere at (a) 200 m and (b) 10 000 m.

FIGURE 17.11 Airfoil performance curves.