Last Updated On [03-11-2023]
For a general aviation airplane with tail efficiency $\eta=0.95$, horizontal tail volume ratio $V_{H}=0.453,$ downwash angle slope $\frac{d \varepsilon}{d \alpha}=0.35,$ wing lift curve slope $C_{L \alpha}^{w}=4.8 \mathrm{rad}^{-1},$ horizontal tail lift curve slope $C_{L \alpha}^{t}=4.4 \mathrm{rad}^{-1},$ shift in neutral point location as a percentage of mean aerodynamic chord is _________(round off to two decimal places).
Question ID - 155410 :- For a general aviation airplane with tail efficiency $\eta=0.95$, horizontal tail volume ratio $V_{H}=0.453,$ downwash angle slope $\frac{d \varepsilon}{d \alpha}=0.35,$ wing lift curve slope $C_{L \alpha}^{w}=4.8 \mathrm{rad}^{-1},$ horizontal tail lift curve slope $C_{L \alpha}^{t}=4.4 \mathrm{rad}^{-1},$ shift in neutral point location as a percentage of mean aerodynamic chord is _________(round off to two decimal places).
For a general aviation airplane with tail efficiency $\eta=0.95$, horizontal tail volume ratio $V_{H}=0.453,$ downwash angle slope $\frac{d \varepsilon}{d \alpha}=0.35,$ wing lift curve slope $C_{L \alpha}^{w}=4.8 \mathrm{rad}^{-1},$ horizontal tail lift curve slope $C_{L \alpha}^{t}=4.4 \mathrm{rad}^{-1},$ shift in neutral point location as a percentage of mean aerodynamic chord is _________(round off to two decimal places).
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A single engine, propeller driven, general aviation airplane is flying in cruise at sea- level condition (density of air at sea-level is $1.225 \mathrm{~kg} / \mathrm{m}^{3}$ ) with speed to cover maximum range. For drag coefficient $C_{D}=0.025+0.049 C_{l}^{2}$ and wing loading $W / S=9844 \mathrm{~N} / \mathrm{m}^{2},$ the speed of the airplane is _________$\quad \mathrm{m} / \mathrm{s}$ (round off to one decimal place).
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