CAJ | 학술논문

为了对通用航空飞行器(CAV)从近连续流到稀薄过渡流气动热特性进行研究,用红外热图技术在地面试验中测量了在典型轨道参数状态下CAV表面的热流分布.首先介绍了气动热试验研究所用的高超声速低密度风洞、红外热像仪等主要仪器设备的性能参数以及高超声速通用航空飞行器模型.其次介绍了高超声速低密度风洞气动热试验采用的3种模拟准则即粘性干扰参数、总焓与壁面焓差参数和克努曾数.最后,在马赫数M肄=7、12,攻角=0毅、12毅、24毅试验条件下,获得了CAV模型迎风面、背风面、侧面典型的流场结构图、红外热图和热流分布,并对CAV模型在不同状态下迎风中心线与翼前缘热流的试验结果、迎风中心线试验结果与工程计算结果进行了比较.研究表明:翼边缘热流大小呈现“马鞍形”分布,攻角变化对气动加热影响比较明显.
위료대통용항공비행기(CAV)종근련속류도희박과도류기동열특성진행연구,용홍외열도기술재지면시험중측량료재전형궤도삼수상태하CAV표면적열류분포.수선개소료기동열시험연구소용적고초성속저밀도풍동、홍외열상의등주요의기설비적성능삼수이급고초성속통용항공비행기모형.기차개소료고초성속저밀도풍동기동열시험채용적3충모의준칙즉점성간우삼수、총함여벽면함차삼수화극노증수.최후,재마혁수M이=7、12,공각=0의、12의、24의시험조건하,획득료CAV모형영풍면、배풍면、측면전형적류장결구도、홍외열도화열류분포,병대CAV모형재불동상태하영풍중심선여익전연열류적시험결과、영풍중심선시험결과여공정계산결과진행료비교.연구표명:익변연열류대소정현“마안형”분포,공각변화대기동가열영향비교명현.
To study the characteristic of aerodynamic heating on common aviation vehicle (CAV) from near continuous flow region to rare transitional flow one, the surface aerodynamic heat flux distribution on CAV was measured in the ground test with infrared thermographic technique under the typical orbital parameter conditions. The function and parameter of hypersonic low density wind tunnel and infrared camera as well as the shape characteristic of the CAV were given in this paper firstly. Three simulation means such as viscous interaction parameter, enthalpy difference between total enthalpy and wall enthalpy and Knudsen number parameter adopted in the hypersonic low density wind tunnel were presented. At the test conditions M∞=7, α=0o, 12o and M∞=12, α=24o, heat transfer distributions on the whole model surface, typical flow field schlieren pictures and infrared mappings were obtained. The heat transfer results at the model windward centerline, windward wing forward edge and theoretical computation were compared at different Mach number and different attack angle. Test result shows that heat flux distributions on windward wing forward edge possesses of shape as saddle, that the influence of the variety of attack angle on aerodynamic heating is distinct.