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Unformatted text preview: (b) Use the exact (shock-expansion) theory to nd the static pressure ratio p/p 1 in regions 2, 3, and 4. (c) Using linear theory, nd 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 coecients are C l = L 1 2 1 U 2 1 c = L 1 2 p 1 M 2 1 c C d = D 1 2 1 U 2 1 c = D 1 2 p 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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This note was uploaded on 08/31/2010 for the course ENGRMAE 135 taught by Professor Staff during the Spring '08 term at UC Irvine.
- Spring '08