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Unformatted text preview: 3. Consider a propeller driven aircraft with the following characteristics: Drag polar: Weight @ beginning of cruise = 2950 lb. Wing area, S = 174 ft 2 Propeller efficiency, η = 0.8 Specific fuel consumption, c = 2.25*10-7 ft-1 It has been determined that the minimum amount of fuel needed to cruise a specified range is 367 lb. As a trade-off study, you have been asked to select a turbojet engine instead of the propeller engine. Determine the upper limit on the sfc (i.e., c t ) the turbojet engine should have to cover at least the same range with the same amount of fuel at sea level (sea level density is 0.002377 slug.ft-3 )...
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This note was uploaded on 04/26/2011 for the course MEM 425 taught by Professor Yousuff during the Spring '08 term at Drexel.
- Spring '08