• 作者： 朱信
• 作者服務機構： 國立臺灣大學機械工程學系
• 中文摘要： 升力面在非穩定流中，其尾跡係由相當複雜的渦流系組合而成。?了避免計算尾跡中所有渦流元件個別影響的繁複工作 本文中提供一種以升力面表面負荷作?邊界條件而直接計算流場中擾動壓力的方法。這個方法首先以坐標的轉換將控制方 式簡化?聲波方程式的形式，然後再以聲源及聲偶的組合以求出一個通解。聲源及聲偶的大小分佈則配合已知的升力面上 負荷條件。應用這個結果，可以求出飛行體作不穩定飛行時，翼上負荷所導致的機身上壓力變化，從而求出機翼與機體間 干?效應。
• 英文摘要： The subsonic unsteady flow is characterized by the phenomenon that there is a complicated wake system consisting of both trailing and shedding vortices behind lifting surfaces. Therefore, in order to avoid the impractical task of applying Biot-Savart law to each vortex element of this wake system, the perturbation pressure in the flow field is determined directly by formulating a boundary-value problem with unsteady pressure distributions on lifting surfaces as boundary conditions. In this approach, Galilean-Lorentz transformation is first taken to reduce the governing equation to the form of an acoustic wave equation. Then a general solution is obtained by superimposing acoustic sources and/or doublets, with their respective strengths being the Neumann and/or Dirichlet boundary conditions in the transformed space. By applying the result obtained, the pressure distribution on the body surface of a wing-body combination, which is induced by the unsteady airload acting on the wing, can be calculated. The wing-body interaction in unsteady flow can thus be determined.
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