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).

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