A prototype jet-powered UAV has a wing planform with S = 60 ft2 and b = 20 ft. and an Oswald efficiency of e = 0.82. The aircraft has CD,0= 0.04. The weight is 2,000 lb. For this aircraft, determine the following:a. Minimum thrust required at sea level for steady level flight.b. Velocity of minimum thrust required for the conditions in (a).c. The induced drag for the conditions in (a).d. If Vmax at sea level is 550 fps, what is the thrust available in lb?e. Given the thrust available is produced by a single turbojet engine with a cross-sectional inlet area of Ain= 2.5 ft2, determine the exit velocity from the engine and the propulsion efficiency assuming the exit pressure is atmospheric.. d. If Vmax at sea level is 550 fps, what is the thrust available in lb?e. Given the thrust available is produced by a single turbojet engine with a cross-sectional inletarea of Ain= 2.5 ft², determine the exit velocity from the engine and the propulsion efficiencyassuming the exit pressure is atmospheric.. A prototype jet-powered UAV has a wing planform with S = 60 ft2 and b = 20 ft. and an Oswaldefficiency of e = 0.82. The aircraft has CD,0= 0.04. The weight is 2,000 lb. For this aircraft,determine the following:a. Minimum thrust required at sea level for steady level flight.b. Velocity of minimum thrust required for the conditions in (a).c. The induced drag for the conditions in (a).

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Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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A prototype jet-powered UAV has a wing planform with S = 60 ft2 and b = 20 ft. and an Oswald efficiency of e = 0.82. The aircraft has CD,0= 0.04. The weight is 2,000 lb. For this aircraft, determine the following:

a. Minimum thrust required at sea level for steady level flight.

b. Velocity of minimum thrust required for the conditions in (a).

c. The induced drag for the conditions in (a).

d. If Vmax at sea level is 550 fps, what is the thrust available in lb?

e. Given the thrust available is produced by a single turbojet engine with a cross-sectional inlet area of Ain= 2.5 ft2, determine the exit velocity from the engine and the propulsion efficiency assuming the exit pressure is atmospheric..

A prototype jet-powered UAV has a wing planform with S = 60 ft2 and b = 20 ft. and an Oswald
efficiency of e = 0.82. The aircraft has CD,0= 0.04. The weight is 2,000 lb. For this aircraft,
determine the following:
a. Minimum thrust required at sea level for steady level flight.
b. Velocity of minimum thrust required for the conditions in (a).
c. The induced drag for the conditions in (a).

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