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Unformatted text preview: (b) Use the exact (shock-expansion) theory to ²nd the static pressure ratio p/p 1 in regions 2, 3, and 4. (c) Using linear theory, ²nd an approximate value For static pressure ratio p/p 1 in regions 2, 3, and 4. TURN PAGE 1 (d) To compute the lift and drag of the airfoil, we Frst calculate the force (per unit span) acting on each airfoil surface (since these are pressure forces, they act normal to the surface). Summing the force components normal to ±ow direction gives the lift L . Summing the force components parallel to ±ow direction gives the drag D . The non-dimensional lift and drag coe²cients are C l = L 1 2 ρ 1 U 2 1 c = L 1 2 γp 1 M 2 1 c C d = D 1 2 ρ 1 U 2 1 c = D 1 2 γp 1 M 2 1 c where c is the chord length. Compute C l and C d based on (i) the exact theory and (ii) on the linear theory. 2...
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- Spring '08
- Aerodynamics, Mach number, static pressure ratio, pressure ratio p/p1, planar supersonic nozzle