飞机机身腹部与两侧进气道性能比较试验研究

Comparision of Inlet Performance with the underfuselage Inlet and Fuselage Side Inlets

通过高低速风洞试验,对比迎角和侧滑角对机身腹部和机身两侧进气的进气道气动性能的影响。试验结果表明:在超音速来流状态下,当迎角增加到5°时,腹部进气道的气动性能改善,而两侧进气道的气动性能几乎不变;在亚音速来流状态下,当迎角从6°逐渐增加到所试验的值(高亚音速为12°,低速为30°),两侧进气道的气动性能逐渐明显变差,而腹部进气道的气动性能对迎角并不敏感,基本能保持无迎角时的性能;在高低速来流状态下,两种型式进气道的气动性能对所试验的侧滑角β(小于6°或9°)均不敏感。

The measurement accuracy of a wind tunnel balance is the key factor to improve the measurement accuracy for a test model in the wind tunnel. In order to improve the measurement accuracy of the wind tunnel balance, a great deal of investigation is carried out in China. This paper summarizes a program to improve the measurement accuracy of wind tunnel balances. In the program, the investigation is carried out in three aspects: (1) designing a drag component of the balance in low interactions; (2) choosing high quality foil strain gauges with temperature self-compensation; (3) choosing the excellent gauges and mounting them meticulously. As an example, these research achievements are applied in a 18 six component balance. The measurement accuracy of a GB-04 standard model in a transonic wind tunnel with the 18 six component balance comes up to the advanced world standard.