Consider In The Figure The Flat Plate Airfoil In Supersonic Flow Moo 0 The Mach Numbers And Static Pressure Ratios 1 (105.25 KiB) Viewed 35 times
Consider in the figure the flat-plate airfoil in supersonic flow (Moo > 0). The Mach numbers and static-pressure ratios on the upper (region 1) and lower (region 2) surfaces, respectively, are also given in the figure. Determine: 1. The freestream Mach number (Moo) and the airfoil's angle-of-attack (a). 2. The airfoil's lift (C) and wave-drag (Caw) coefficients. 3. The static-pressure ratios of regions 3 and 4: (P3/Poo) = (P4/Poo). 4. Mach numbers in regions 3 (M3) and 4 (Ma). 5. The flow turning angles: 103 = 204. 6. The slip-line's upwash angle, Quw, (relative to the horizontal reference line).
F expansion L=? Moo =? oblique M = 5.57428061 P/P = 0.2869401635 0 ® . Slip line LON oblique Shock M2 = 3.65083126 P2/P, = 2.76417243 Pexpansion an
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