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Unformatted text preview: it iiii'isii‘tfieti MAE 261 Test #2 March 16, 2005
Open Notes and Textbook
1. An airplane has a wing with AR m 7. A model of the airplane is tested in a
subsonic wind tunnel with the following resuits: Angie of attack, deg. Lift Coefficient Drag Coefficient a) Calcutate the Iift~curve slope and the angle of zero iift. b) Caiculate 09,9 and efficiency factor, e. 2. Ar: airplane has RICmax = 2500 ft/min at sea level. Assume that it
decreases My with altitude from sea ievel up to the absolute ceiling,
which is 30,000 it. 3) Determine the equation for RICmax as a function of attitude.
b) Determine the altitude of the service ceiling.
0) Calculate the minimum time to climb to the service ceiiing. 3. The Piper Arrow is to be outfitted with a new engine that wiii produce a
maximum speed of 275 ft/sec for a weight of 2750 lb at sea level. Assume
that all the characteristics of the airpiane remain the same except for
engine bhp. Sm170 ftz, AR=7.372, em0.?, 00,0m0.027, {120.75. a) Caicuiate CL and CD for ievel ﬂight at 275 ft/sec at sea levei.
b) Calculate the sea level bhp needed for the new engine. 4. 3) Calculate (LID)max for the Piper Arrow.
t3) The Piper Arrow has a fuei tank capacity of 72 gallons of aviation fuei,
which weighs 5.64 lb/gal. Caicuiate the weight, W1, at end of a ﬂight
segment which starts with We a 2750 Eb and ends with a 6% fuel reserve.
0) Caicuiate the maximum range, using SFC=O.45 ibf/(hnhp). . GLUTEG H .T$._._.MAE.._... "TEST ﬁ’Z 1 .. {L 3 _. géj’i‘ﬁﬁ . _. .. w = a 7 .c ‘ . . : w CE 8 Ma 0.3.7. ,M 14:; if” 8 AR "594 3'6
. r: h I: M I I .... _ .fi ...
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 Spring '06
 DeJarnette

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