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Unformatted text preview: smartest MAE 261 HW #5  DUE 03«0206 Consider the same singleengine light generalaviation airplane, patterned
after the Piper Arrow, as HW #4, which had the following characteristics: 3 = 170 a2, ‘0 m 35.4 a, e = 0.70, w n 2750113, cm, = 0.027 Engine maximum power at standard sea level is 200 hp. Assume the power
of the engine is proportional to atmospheric density at altitude. The propeller
efﬁciency is n = 0.75 and maximum lift coefﬁcient = 2.200. 1. Calculate the maximum and minimum equivalent airspeeds, in mph,
for level flight at standard sea level, 10,000 ft and 22,000 ft. Solve for
them from the power available m power required equation. 2. Calculate the atmospheric density at the absolute and service ceilings
for this airplane. Then interpolate the table in Appendix B to
determine the standard altitude of the absolute and service ceilings. 3. Develop a computer program or spreadsheet to calculate, tabulate and
plot the maximum rate of climb (in ft/min) and minimum time to
climb (minutes) as a function of altitude from standard sea level to the
nearest altitude increment below the absolute ceiling. Use altitude
increments of 2,000 ft. You will need a secondary vertical axis for the
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This note was uploaded on 03/28/2008 for the course MAE 261 taught by Professor Dejarnette during the Spring '06 term at N.C. State.
 Spring '06
 DeJarnette

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