CAJ | 학술논문

通过数值模拟方法研究了小展弦比飞翼标模在0．6、0．9、1．5三个典型马赫数下的支撑干扰特性，分别考虑了近场尾部外形局部畸变和尾支杆干扰及远场风洞中部支架干扰，并基于表面压力系数差异为准则尝试对近场干扰量进行分解。研究得到如下结论：马赫数0．6时，远场支撑阻力系数和俯仰力矩系数的干扰量约占总支撑干扰量的30％，升力系数约占20％；马赫数0．9、迎角2°时，阻力系数远场支撑干扰量占总支撑干扰量的40％，迎角18°时，远场支撑干扰使得涡破裂位置提前；马赫数1．5时，远场支撑干扰可以忽略；基于表面压力系数差异将支撑干扰量分解的方法在亚声速支撑干扰前传明显时不适用，在马赫数0．9、迎角2°时求得近场支撑干扰使得马赫数减小约0．02，迎角减小约0．1°，马赫数1．5时用此法求得马赫数和迎角的干扰量均约等于0。
통과수치모의방법연구료소전현비비익표모재0．6、0．9、1．5삼개전형마혁수하적지탱간우특성，분별고필료근장미부외형국부기변화미지간간우급원장풍동중부지가간우，병기우표면압력계수차이위준칙상시대근장간우량진행분해。연구득도여하결론：마혁수0．6시，원장지탱조력계수화부앙력구계수적간우량약점총지탱간우량적30％，승력계수약점20％；마혁수0．9、영각2°시，조력계수원장지탱간우량점총지탱간우량적40％，영각18°시，원장지탱간우사득와파렬위치제전；마혁수1．5시，원장지탱간우가이홀략；기우표면압력계수차이장지탱간우량분해적방법재아성속지탱간우전전명현시불괄용，재마혁수0．9、영각2°시구득근장지탱간우사득마혁수감소약0．02，영각감소약0．1°，마혁수1．5시용차법구득마혁수화영각적간우량균약등우0。
Support interferences of low-aspect-ratio flying-wing at M=0.6,0.9 1.5 are cal-culated by means of numerical simulation methods,both near-field interference and far-field in-terference are concerned,and attempt is made to analyse mean flow distortion distribution for the model.Results show that,drag coefficient and pitching moment coefficient of far-field interfer-ence account about 30% of the total support interference while lift coefficient account about 20%at M=0.6.For Mach number 0.9,angle of attack 2°,drag coefficient of far-field interference ac-count 40%,and far-field interference make the vortex breakdown location move ahead at the an-gle of attack 18°.Far-field interference can be ignored at M=1.5.It’s hard to get the distortion of Mach number and angle of attack (△M and △α)at subsonic speed (M=0.6);when upstream become M=0.9,support interference affects the shock position,and the surface pressure coeffi-cient differences are sensitive with Mach number,support interference decrease the Mach number for about 0.02 and decrease the angle of attack for 0.1°on the model surface.