摘要
尾喷流对升力体高超声速飞行器的气动特性影响显著,风洞喷流模拟测力试验是研究升力体飞行器尾喷流干扰效应的重要手段。在尾喷流模拟气动力试验中,选取恰当的喷流模拟参数,以及克服喷流供气管路对天平测力的干扰以提高测量精准度,是需要解决的关键技术。在CARDC的Ф1米高超声速风洞中,研究了采用冷喷流模拟、飞行器整体模型测力的升力体飞行器尾喷流模拟测力试验方法。通过优化模型结构设计、选用小干扰的喷管分断缝隙密封措施,解决了带尾喷流模拟条件下的升力体飞行器气动力精确测量问题,提高了带喷流气动力试验数据精度,接近常规气动力试验的水平。
The exhaust flow induced by aft-body nozzle of lifting-body hypersonic air-breathing vehicle interacts with the aerodynamic characteristics of the vehicle dramatically,and the wind tunnel jet simulation aerodynamic test is an important method to investigate such interaction effect.Besides the simulation criteria,it＇s the key technique to ensure the data accuracy and precession in those tests,avoiding the interaction between air-supply device and balance measurement.A wind tunnel experimental technique investigation on after-body jet simulation aerodynamic force test has been conducted in 1m hypersonic wind tunnel of CARDC.With optimized model design and model-nozzle separation gap seal measures,the test data precession and uncertainty level have been enhanced proximity to that of conventional aerodynamic force test.
出处
《空气动力学学报》
CSCD
北大核心
2016年第1期86-90,共5页
Acta Aerodynamica Sinica
关键词
吸气式飞行器
升力体
喷流模拟
气动力
风洞试验技术
airbreathing vehicle
lifting-body
jet simulation
aerodynamic forces
wind tunnel test technique
