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7.1.6: Performances in gliding

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    In all generality, a glider is an aircraft with no thrust. In stationary linear motion in vertical plane, the equations are as follows:

    \[D = mg \sin \gamma,\]

    \[L = mg \cos \gamma,\]

    and dividing:

    \[\tan \gamma_d = \dfrac{D}{L} = \dfrac{C_D}{C_L} = \dfrac{1}{E(\alpha)},\]

    截屏2022-01-31 下午10.32.31.png
    Figure 7.3: Aircraft forces in a horizontal loop.

    where \(\gamma_d\) is the descent path angle \((\gamma_d = -\gamma)\). As in stationary linear-horizontal flight, in order to increase the velocity of a glider it is necessary to reduce the angle of attack. Moreover, the minimum gliding path angle will be obtained flying with the maximum aerodynamic efficiency. The descent velocity of a glider \((V_d)\) can be defined as the loss of altitude with time, that is:

    \[V_d = V\sin \gamma_d \cong V \gamma_d.\]

    7.1.6: Performances in gliding is shared under a CC BY-SA 3.0 license and was authored, remixed, and/or curated by Manuel Soler Arnedo via source content that was edited to conform to the style and standards of the LibreTexts platform; a detailed edit history is available upon request.