CAJ | 학술논문

高速飞行器的体-翼干扰区热流精确预测对于飞行器生存能力与战术性能的提高具有重要的意义,是高性能飞行器设计水平的一个重要标志.由于体-翼干扰区流场的复杂性,目前尚无满足工程设计要求的热环境预测方法,在分析体-翼流场特性的基础上应用文献[1]的压力-热流关系式,提出体-翼干扰区的热流预测方法,即压力由N-S数值解给出,热流应用压力-热流关系式得到,炮风洞的实验结果验证了本文预测方法的可靠性.
고속비행기적체-익간우구열류정학예측대우비행기생존능력여전술성능적제고구유중요적의의,시고성능비행기설계수평적일개중요표지.유우체-익간우구류장적복잡성,목전상무만족공정설계요구적열배경예측방법,재분석체-익류장특성적기출상응용문헌[1]적압력-열류관계식,제출체-익간우구적열류예측방법,즉압력유N-S수치해급출,열류응용압력-열류관계식득도,포풍동적실험결과험증료본문예측방법적가고성.
It is significant that accurate forecast of heat flux on the body-wing interaction region of high speed vehicle, which will improve its viability and capabilities of fighting, indicate the ability of high-powered vehicle design.There is no effective fore-cast method of thermal environment presently because of the complexity of flow field at the body-wing interaction region. On the basis of the analysis about characteristic of the flow field at body-wing interaction region, the pressure-heat flux relation formula from referenced[1] ,a new forecast method of heat flux was introduced, that is, the pressure were solved by N-S numerical method and the heat flux was presented by pressure-heat flux relation formula. The resuhs of experiment done in the gun tunnel can vali-date the reliability of the forecast method introduced by this paper.