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Question: pitchingmoment coefficient vs lift coefficient data of an aircraft at...

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Pitching-moment coefficient vs lift coefficient data of an aircraft at various fixed elevator deflections are given in the figure below. a. Determine the stick-fixed neutral point of the aircraft and its static margin. Is the aircraft statically stable longitudinally? b. If the aircraft is to be flown steady and level at 38.4 m/s, determine the trim lift coefficient and the elevator angle to trim.

c. Estimate the elevator control power of the aircraft from the figure. Hint: Determine the d. If the elevator control power of the aircraft is as calculated above and the maximum , determine the most forward CG location so that the change in Cm values with the change of de for a fixed Ci value. +20° elevator deflection is δ. aircraft can be trimmed at its maximum lift coefficient of 1.4. of the aircraft? a30 e. What is the range of CG location to satisfy longitudinal static stability and trim requirement 0.15 Weight 12,237 N Wing area 17 m2 Xc,-25% MAC 0.10 0.05 CL mcg 0.0 -0.05 -0.10 -0.15 0.2 0.40.6 0.8 10 δ,--15° oe-10° 2-0。

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