Aerospace Engineering > GATE 2017 > Longitudinal Stability and Control
A conventional aircraft was analyzed to estimate the contribution of wing towards Cm0 (Cm at α=0) of the whole aircraft. The wing was installed with zero setting angle along the fuselage reference line. Further, the wing was laid such that X¯ac,w=0.3 and X¯cg,aircraft=0.4. X¯ac,w and X¯cg,aircraft are the non-dimensional distances, from the leading edge of the wing. of the aerodynamic center of the wing and center of gravity of the aircraft respectively. The wing had the following aerodynamic characteristics:
CL0=0.20 and Cmac,wing=-0.02.
The numerical value of Cm0,w (contribution of the wing to Cm0) about the CG of the aircraft is _______ (in two decimal places).
CL0=0.20 and Cmac,wing=-0.02.
The numerical value of Cm0,w (contribution of the wing to Cm0) about the CG of the aircraft is _______ (in two decimal places).
Correct : 0.00 to 0.00
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