Question

4.14 A supersonic inlet is to be designed to operate at Mach 3.0. Two possibilities are con- sidered, as shown in Figure 4.48. In one, the compression and deceleration of the flow takes place through a single normal shock (Figure 4.48a); in the other, a wedge-shaped Figure 4.47 A supersonic inlet. M =24 514 Oblique Shock and Expansion Waves 215 M M м. M (b) Figure 4.48 (a) Normal shock diffuser, (b) wedge-shaped diffuser. diffuser (Figure 4.48b) is used and the deceleration is through two weak oblique shocks followed by a normal shock wave. The wedge turning angles are sº each. Compare the loss in stagnation pressure for the two cases. Ans.(a) 0.3283; (b) = 0.5803 Pos Por

GAS DYNAMICS

Answer 1

(9) for at ha 287-18-1977-1 for normal shock diffuser M P2 (8+1) Mi Y+ 1 2+ (8-1)m," Poz P₂ )( a P Pol Si 2 T-1 to 4 6.4 1.4-1)/(1.4+1 ) 3 2 + (1.4-1)3 (2 (1.4)3 - (1.4-1) (1:4 +1) 19 Por 0.3283 Pol

Poz - 0.9794 Pol for Man = 1.26 from normal shock table Poz - 0.9857 Poz for M₂ = 2.26 from normal shock talde Poy Pos 0.6011

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