1.2m×1.2m高速风洞大振幅动态试验系统及其初步应用  

Introduction of dynamic experimental system with large amplitude in the 1.2m×1.2m sub-transonic wind tunnel

作　　者：李其畅[1] 伍开元[1] 赵忠良[1] 郑世华[1] 徐永长[1] 黄存栋[1] 王涛[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2005年第3期378-381,388,共5页Acta Aerodynamica Sinica

基　　金：空气动力学预研基金(863-6-05)

摘　　要：高速大迎角动态气动特性是衡量新一代高机动飞行器性能的重要参数之一。本文简要介绍了在CARDC的1.2m×1.2m高速风洞的大振幅动态试验系统。试验M=0.40,0.60,0.80;振幅为15°3、0°;振动频率分别为0.84Hz、1.47Hz、2.84Hz和4.41Hz。初步分析试验研究所揭示的70°三角翼模型高速大迎角动态气动特性,结果表明:M数、迎角振荡的幅值和K值(振动减缩频率)是影响70°三角翼模型动态迟滞气动特性的主要参数。Dynamic aerodynamics characteristic is one of very important parameters of modern maneuverable aircraft to be scaled at high angle of attack and high speed. The test equipment of 1.2m×1.2m wind tunnel of CARDC for a model pitching oscillation with large amplitude is introduced. The Mach number is 0.40,0.60 and 0,80. The amplitude is 15° and 30°, the oscillation frequencies is 0.8Hz, 1.47Hz, 2.48Hz and 4.41Hz. The dynamic aerodynamics characteristic on pitching oscillation 70-deg delta wing model with large amplitude at high speed is simply analyzed in the paper. The test results indicated that the aerodynamic lag characteristic 70-deg delta wing are dominant rely on the Mach number, the amplitude and reduced frequency of model pitching oscillation.

关 键 词：风洞试验 动态失速 大振幅 俯仰 非定常空气动力 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]