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ÓÐûÓкÃÐÄÈ˰ï½â¸ö¹úÍâ»úеϵÁ÷ÌåÁ¦Ñ§²¿·ÖµÄ¿¼Ì⣬´ð°¸ÖªµÀÁË£¬Çó¹ý³Ì£¬ÖÐÓ¢ÎĽâ´ð¾ù¿É£¬Ð»Ð»ÁË£¡ B1. A stream of air enters a diverging duct with a Mach number of 2.0, a static pressure of 200 kPa, and a static temperature of 350 K. The area of the duct inlet is A1=0.25 m2 and the area of the exit is Ae=0.6 m2. (a) Determine the pressure at the duct exit if the flow is entirely isentropic. (´ð°¸£º45.6kPa) (b) The exit pressure is now increased and a normal shock wave forms at a location in the duct where the cross section area is A2=0.35 m2. Determine the new exit pressure. ´ð°¸£º813kPa |
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