Aerospace Engineering > GATE 2014 > Aircraft Stability
Consider the following four statements regarding aircraft longitudinal stability:
P. CM,cg at zero lift must be positive
Q. ∂CM,cg/∂aa must be negative (aa is absolute angle of attack)
R. CM,cg at zero lift must be negative
S. Slope of CL versus aa must be negative
Which of the following combination is the necessary criterion for stick fixed longitudinal balance and static stability?
P. CM,cg at zero lift must be positive
Q. ∂CM,cg/∂aa must be negative (aa is absolute angle of attack)
R. CM,cg at zero lift must be negative
S. Slope of CL versus aa must be negative
Which of the following combination is the necessary criterion for stick fixed longitudinal balance and static stability?
Correct : c
Similar Questions
For an airplane having directional/weathercock static stability, which of the following options is/are correct?
For a general aviation airplane, one of the complex conjugate pairs of eigenvalues for longitudinal dynamics is given by -0.039 ± 0.0567i (in SI units). If the...
For a longitudinally statically stable aircraft, which one of the following represents the relationship between the coefficient of pitching moment about the cen...
Total Unique Visitors
Loading......