摘要
本文描述了在 FL-1风洞中,对 NACA0012翼型进行的非定常跨音速压力测量实验。实验目的是研究在跨音速风洞中二元机翼非定常压力测量的实验技术问题,包括实验装置的设计、数据采集和处理等。并初步研究了 M 数、攻角、振幅和频率等参数对非定常压力分布的影响。
This paper describes a steady and an unsteady pressureexperiment on a NACA 0012 profile in FL-1 transonic wind tunnel.The purpose of the test is mainly to investigate the problem with te-chniques in unsteady pressure measurement on 2-D profile in transo-nic wind tunnel.It involves the design of experimental equipments,dataacquisition and processing.The test also investigates the influence ofMach number,angle of attack,oscillation amplitude and frequency onunsteady pressure distributions.
关键词
跨音速
非定常压力
风洞
动态测压
transonic wind tunnel
pressure measurement
profile
