A conventional aircraft was analyzed to estimate the contribution of wing towards $C_{m 0}\left(C_{m}\right.$ at $\left.\alpha=0\right)$ of the whole aircraft. The wing was installed with zero setting angle along the fuselage reference line. Further, the wing was laid such that $\bar{X}_{\mathrm{ac}, \mathrm{w}}=0.3,$ and $\bar{X}_{\mathrm{cg} \text { arcrat }}=0.4 . \bar{X}_{\mathrm{ac}, \mathrm{w}}$ and $\bar{X}_{\mathrm{cg}, \text { arcrat }}$ are the nondimensional 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:
$\mathrm{C}_{\mathrm{L} 0}=0.20,$ and $\mathrm{C}_{\text {mac, wing }}=-0.02$
The numerical value of $\mathrm{C}_{\mathrm{m} 0, \mathrm{w}}$ (contribution of the wing to $\mathrm{C}_{\mathrm{m} 0}$ ) about the $\mathrm{CG}$ of the aircraft is____________ (in two decimal places).

Question ID - 155593 | SaraNextGen Top Answer

A conventional aircraft was analyzed to estimate the contribution of wing towards $C_{m 0}\left(C_{m}\right.$ at $\left.\alpha=0\right)$ of the whole aircraft. The wing was installed with zero setting angle along the fuselage reference line. Further, the wing was laid such that $\bar{X}_{\mathrm{ac}, \mathrm{w}}=0.3,$ and $\bar{X}_{\mathrm{cg} \text { arcrat }}=0.4 . \bar{X}_{\mathrm{ac}, \mathrm{w}}$ and $\bar{X}_{\mathrm{cg}, \text { arcrat }}$ are the nondimensional 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:
$\mathrm{C}_{\mathrm{L} 0}=0.20,$ and $\mathrm{C}_{\text {mac, wing }}=-0.02$
The numerical value of $\mathrm{C}_{\mathrm{m} 0, \mathrm{w}}$ (contribution of the wing to $\mathrm{C}_{\mathrm{m} 0}$ ) about the $\mathrm{CG}$ of the aircraft is____________ (in two decimal places).