aircraft_maneuvering_performance

aircraft_maneuvering_performance - Virginia Tech - Air...

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Unformatted text preview: Virginia Tech - Air Transportation Systems Laboratory Example of Aircraft Climb and Maneuvering Performance CEE 5614 Analysis of Air Transportation Systems Dr. Antonio A. Trani Professor Virginia Tech - Air Transportation Systems Laboratory Example - Aircraft Climb Performance • Aircraft maneuvering performance analysis (initial climb profile) • Use the the vehicle characteristics for the very large capacity transport aircraft in the Matlab files for CEE 5614 to solve this problem (http://128.173.204.63/courses/cee5614/ cee5614_pub/AirbusA380_class.m ) 2 A B C D Virginia Tech - Air Transportation Systems Laboratory Departure Procedure (Sample Airport) source: Google Earth (2009) Airport Departure Track 3 A B C D Virginia Tech - Air Transportation Systems Laboratory Problem Description • The aircraft climbs at 180 knots (IAS) with 10 degrees of flaps down after departure as shown in the diagram • As the aircraft climbs past the runway threshold at an altitude of 100 meters (and with the landing gear already retracted), the aircraft loses the inner starboard engine • The pilot flies the departure profile shown in the figure to avoid terrain around the field. • With the wing flaps deflected, the aircraft drag polar is modified with an extra term as follows: 4 Virginia Tech - Air Transportation Systems Laboratory Modifed Drag Function • Drag polar with an added term to account for drag due to flaps: 5 C d = C do + C di + C df C d = C do ( M ) + C l 2 π A Re + C df where: C d = total drag coefficient (dim) C do = zero lift drag coefficient (lift independent) (dim) C di = induced drag coefficient (lift dependent) (dim) C df = drag coefficient due to flaps (dim) AR = wing aspect ratio (dim) e = efficiency factor (dim) C l = lift coefficient (dim) Virginia Tech - Air Transportation Systems Laboratory Example - Aircraft Climb Performance Data File • Very large capacity transport aircraft (http://128.173.204.63/ courses/cee5614/cee5614_pub/AirbusA380_class.m ) geometric, mass and speci¡c fuel consumption drag data engine thrust data speed pro¡le data 6 Virginia Tech - Air Transportation Systems Laboratory Effects of Wing Flaps on C df • The following table provides values of the drag coefficient due to flaps for various flap angles • Note that flap setting are discrete and unique to each aircraft 7 Flap Angle (degrees) C df 2 0.006 5 0.010 10 0.015 20 0.023 Virginia Tech - Air Transportation Systems Laboratory...
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This note was uploaded on 12/31/2011 for the course CEE 5614 taught by Professor Staff during the Fall '10 term at Virginia Tech.

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aircraft_maneuvering_performance - Virginia Tech - Air...

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