The SR-71 Blackbird is the fastest production plane capable of reaching speeds of more than Mach 3, roughly 3000 kph. If a Blackbird is cruising at a speed of 585 m/s an altitude of 33,435 ft and assumin it produces a Normal Shockwave in the process, what would be its downstream Mach number? Note: Specific Heat of Air, R= 287 J/kg"K
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- The Mach no. of a fixed geometry inlet at overspeeded for starting mode (Ai= 0.13 m2, ,At= 0.095 m2) 0.41 O 2.77 O 1.72 O 0.49 OA normoa shock wave exists in air flow with up stream M=2 and a pressure of 20kpa and temperature of 15 c find the Mach number pressure stagntion pressure temperature stagntion temperature and air velocity down stream of the shock WaveConsider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of 30,000-ft, assuming weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, ??? = 0.015, and K = 0.08 a. The thrust required at 30,000-ft. (in pounds)
- The reservoir pressure and temperature for a Laval nozzle are 5 atm [abs] and 520 K,respectively. The flow is isentropically expanded to supersonic speed at the nozzle exitwith area Ae = 4in2. If the exit-to-throat area ratio is 2.295, calculate the followingexit properties: a) Me; b) pe; c) Te; gamma = 1.4, R=287 J/kgKhe reservoir pressure and temperature for a Laval nozzle are 5 atm [abs] and 520 K,respectively. The flow is isentropically expanded to supersonic speed at the nozzle exitwith area Ae = 4in2. If the exit-to-throat area ratio is 2.295, calculate the followingexit properties: d) ρe; e) p0,e; f) T0,e; gamma = 1.4, R = 287 Please show all work!!The scramjet of Fig. operates with supersonic fl owthroughout. Assume that the heat addition of 500 kJ/kg,between sections 2 and 3, is frictionless and at constantarea of 0.2 m2. Given Ma2 = 4.0, p2 = 260 kPa, and T2 =420 K. Assume airflow at k = 1.40. At the combustionsection exit, find (a) Ma3, (b) p3, and (c) T3.
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