飞行动力学

飞行动力学

\[\frac{x'_{np}}{\bar{c}} = \frac{x{np}}{\bar{c}} - V_h \eta_h \frac{a_h}{C_{L\alpha_w}} \tau_e \frac{C_{h\alpha}}{C_{h\delta_e}} \]

\[\frac{x'_{np}}{\bar{c}} = 0.498 - 0.5 \times 0.95 \times \frac{3.867}{5.026} \times 0.6 \times \frac{-0.05}{-0.15} = 0.498 - 0.073 = 0.425 \]

\[C_{m_{C_L}} = \frac{dC_m}{dC_L} = \frac{C_{m\alpha}}{C_{L\alpha}} = -\left( \frac{x_{np}}{\bar{c}} - \frac{x_{cg}}{\bar{c}} \right) = -SM \]

\[C_{m_{C_L}} = -0.248 \]

\[a_h = \frac{a_0}{1 + \frac{a_0}{\pi e AR_h}} = \frac{2\pi}{1 + \frac{2\pi}{\pi \times 0.8 \times 4}} = \frac{6.283}{1 + 0.625} = 3.867 \text{ /rad} \]

\[\frac{x_{np}}{\bar{c}} = \frac{x_{ac_{wf}}}{\bar{c}} + V_h \frac{a_h}{C_{L\alpha_w}} \eta_h \left( 1 - \frac{d\epsilon}{d\alpha} \right) \]

\[\frac{x_{np}}{\bar{c}} = 0.25 + 0.5 \times \frac{3.867}{5.026} \times 0.95 \times (1 - 0.320) = 0.25 + 0.248 = 0.498 \]

\[\frac{x'_m}{\bar{c}} = \frac{x'_{np}}{\bar{c}} - \frac{C_{m_q}}{2 \mu_c} \left(1 - \frac{C_{h_q}}{C_{h_{\delta_e}}} \frac{C_{m_{\delta_e}}}{C_{m_q}}\right) \]

\[C_{L\alpha_w} = \frac{2\pi}{1 + \frac{2\pi}{\pi \times 0.8 \times 10}} = \frac{6.283}{1 + 0.25} = 5.026 \text{ /rad} ) \]

\[C_{m_{\delta_e}} = -0.5 \times 3.867 \times 0.95 \times 0.6 = -1.102 \text{ /rad} \]

2.飞机的飞行性能 （4）

2.2.续航性能-2

关注： 航程与航时

航程关注的是水平距离

一些公式推导————巡航段航程航时计算 &rarr 久航速度与远航速度

应用：最大作战半径（航程）计算————通过公式，代入前后飞机剩余质量（积分中变量是质量）求解