Which of the following is correct to trim an aircraft at positive AOA? – McqOptions

MCQOPTIONS

1.	Which of the following is correct to trim an aircraft at positive AOA?
A.	Cm0 > 0
B.	Cm0 < 0
C.	Cm0 will not affect positive trim AOA
D.	Every value of cm0 will trim at positive AOA
Answer» B. Cm0 < 0

Discussion

No Comment Found

Related MCQs

Which of the following is correct to trim an aircraft at positive AOA?
Determine the corrections or otherwise of the following Assertion [A] and Reason [R]:Assertion [A]: For longitudinal static stability of an aircraft, slope of moment curve should be negative.
Elevator control power is given by _____
If CM0 is -0.052 and lift coefficient at zero angle CL0 is 0.92 then, find CMac. Consider rectangular wing.
A rectangular wing has chord of 2m. Fond neutral point for this wing.
Find the appropriate value of pitching moment coefficient derivative if lift curve slope is 0.032 per degree and Xcg is 0.3. Consider neutral point is located at 60 % of chord from leading edge.
If SM = 0.12 and cg is located at 20% chord from l.e. then, find appropriate neutral point location.
Determine required static margin if lift curve slope is 6.5 per rad and pitching moment coefficient slope as -0.58 per rad.
Determine trim angle if, trim lift coefficient is 0.75 and lift curve slope is 4.5per rad. Consider elevator deflection as 1.056 per rad and trim elevator angle of 0.020 rad.
Thrust will affect the stability of the aircraft.