Consider the supersonic flow over a flat plate at an angle of attack, as sketched in Figure 9.35. As stated in Section 9.7, the flow direction downstream of the trailing edge of the plate, behind the trailing edge shock and expansion waves, is not precisely in the freestream direction. Why? Outline a method to calculate the strengths of the trailing edge shock and expansion waves, and the direction of the flow downstream of the trailing edge

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M₁ = 10 P₁ = 1 atm M₁ = 10 P₁ = 1 atm Compression wave (a) Isentropic compression corner Shock wave (b) Shock compression corner Figure 9.35 Figures for (a) Example 9.9 and (b) Example 9.10. 0=15° 0=15°