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俄罗斯中央空气动力研究院在大量风洞试验与飞行试验基础上得到的飞机各部件阻力系数解析计算方法。该方法可按给定的几何形状计算飞机的巡航阻力系数。文中还介绍了如何使用该方法进行飞机模型在风洞试验条件下得到的阻力系数换算至实际工作条件下的飞机阻力系数。本文的方法适用于展弦比为6～10,后掠角为25°～35°的高亚音速民用飞机,升力系数范围为0～0.6。
Analysis and Calculation Method of Resistance Coefficient of Aircraft Components Obtained by Russia Central Aerodynamics Research Institute Based on a Large Number of Wind Tunnel Tests and Flight Tests. This method calculates the cruise resistance coefficient of the aircraft for a given geometry. The paper also describes how to use this method to convert the drag coefficient of aircraft model under wind tunnel test conditions to the drag coefficient of aircraft under actual working conditions. The method of this paper is suitable for high subsonic civil aircraft with aspect ratio of 6 ~ 10 and sweep angle of 25 ° ~ 35 °, and the lift coefficient range is 0 ~ 0.6.