摘要
本文以J-7飞机为典型,阐述了如何将高速风洞飞机模型的极曲线实验结果修正到真实飞机的实际飞行状态。提出了应进行的修正项目、内容、步骤和具体方法。结果表明,经修正的飞机零升阻力和平衡升致阻力与资料值(经飞机性能试飞验证的结果)有较好的一致性。
Taking J-7 aircraft as a typical example, this paper describes how to correct high speed wind tunnel test results of polars of aircraft models to the real flight conditions, and gives the relative items to be corrected, together with the procedures and concrete methods. It has been shown that the corrected drag at zero-lift and the trimmed drag due to lift are in good agreement with those verified by flight tests for aircraft performance.
出处
《飞行力学》
CSCD
北大核心
1989年第3期11-27,共17页
Flight Dynamics
