Consider a flat plate at an angle of attack in a hypersonic flow. As the angle of attack is increased from zero, the lift coefficient first increases, then reaches a maximum value, and then decreases as the angle of attack continues to increase (as shown in Figure 15.11). Using newtonian theory, prove that the maximum value of the lift coefficient occurs at an angle of attack of \(54.7^{\circ}\).

Figure 15.11:

Transcribed Image Text:

10 9.0 8.0- 0.8 7.0- 0.7 6.0 0.6 LD 5.0 4.0 T 0.5 C HO 0.4- C 3.0- 0.3- 2.0 0.2 1.0 0.1 M1 a 0 15 30 45 60 D 75 90 Angle of attack a, degrees 2.0 1.6 1.2 Cp 0.8 0.4