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MEM425F09.HW4.soln

MEM425F09.HW4.soln - In this condition Hence from(F1...

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Home work #4 (due 10/22/09) Relevance to Program Outcomes a-k : a, e, k --------------------------------------------------------------------------------------------------------- 1. Consider the jet aircraft CJ-1 (relevant parameters given below) initiating a power-off glide from an altitude of 10,000 ft. (density: 0.0017556 slug.ft -3 .) Calculate the glide angle, range along the ground, and the sink rate for each of the following cases: a. maximum glide range b. maximum glide endurance Relevant parameters: parasite drag coefficient: 0.02 Oswald efficiency factor: 0.81 wing span: 53.3 ft. wing area: 318 ft 2 . weight: 19815 lb. 2. Problems from Text: 5.2, 5.3, and 5.5.

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solution 1. Formulas to be used: F1. F2. F3. 1a. Max glide range corresponds to (C L /C D ) max . In this condition Hence, from (F1), From (F2), From (F3), 1b. Max glide endurance flight corresponds to

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Unformatted text preview: In this condition Hence, from (F1), From (F2), From (F3), 5.2 (see example 5.6) Use the expression for “q” from class notes “FillIns” or eqn. (5.50) . For a jet engine , the thrust varies proportional to density as indicated in the class notes and by eqn. (3.19). Eqn (5.50), written in more compact form, as in class notes, is . The available thrust T at sea level (density ρ = 0.002377 slug.ft-3 ) is 202 lb. The available thrust at 10,000 ft (density = 0.0017556 slug.ft-3 ) is With these values substituted, one obtains at sea level, and . 5.3 Eqn(5.43) yields, which in turn yields Since velocity in cruise flight is use of Eqn.(5.44) results in 5.5 The relevant parameters are: b) c) and d) Velocity Expression Sea level 10,000 ft 194 ft/sec 255.3 ft/sec 225.7 ft/sec 297 ft/sec...
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MEM425F09.HW4.soln - In this condition Hence from(F1...

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