CAJ | 학술논문

为研究翼身相对厚度对小展弦比飞翼布局气动特性以及涡流特性的影响，基于已有试验结果的翼身相对厚度为0．16的65°后掠小展弦比飞翼布局，在保持前缘半径和外翼剖面形状相同情况下，通过降低飞翼布局的翼身厚度使其翼身相对厚度为0．08，在马赫数0．9条件下开展了翼身相对厚度影响的数值模拟研究。数值模拟结果表明，在相同迎角条件下，翼身相对厚度对飞翼布局前缘涡在翼面上形成的位置和涡强有较大的影响，翼身相对厚度较小时前缘涡形成的位置越靠近前缘；在前缘（约 x／Cr ＝0．25之前）翼身相对厚度较小布局的涡核强度明显高于翼身相对厚度较大布局，且在前缘涡破裂之前，翼身相对厚度较小布局涡核强度沿弦向变化较为平缓，升力线斜率下降迎角较翼身相对厚度较大布局推迟约8°。研究结果还表明跨声速时，前缘涡的破裂主要与激波的干扰有关，当前缘涡穿过激波时，涡强和涡核轴向速度迅速降低，当涡核轴向速度降为0时，前缘涡破裂。
위연구익신상대후도대소전현비비익포국기동특성이급와류특성적영향，기우이유시험결과적익신상대후도위0．16적65°후략소전현비비익포국，재보지전연반경화외익부면형상상동정황하，통과강저비익포국적익신후도사기익신상대후도위0．08，재마혁수0．9조건하개전료익신상대후도영향적수치모의연구。수치모의결과표명，재상동영각조건하，익신상대후도대비익포국전연와재익면상형성적위치화와강유교대적영향，익신상대후도교소시전연와형성적위치월고근전연；재전연（약 x／Cr ＝0．25지전）익신상대후도교소포국적와핵강도명현고우익신상대후도교대포국，차재전연와파렬지전，익신상대후도교소포국와핵강도연현향변화교위평완，승력선사솔하강영각교익신상대후도교대포국추지약8°。연구결과환표명과성속시，전연와적파렬주요여격파적간우유관，당전연와천과격파시，와강화와핵축향속도신속강저，당와핵축향속도강위0시，전연와파렬。
Various studies have been conducted on the aerodynamic and vortex flow charac-teristics of 65°swept delta wing or flying-wing configurations with relatively small thickness ratio of the inner wing/body part by both experimental and numerical methods.However,in transonic flow field,wing-body thickness has great influence on the introduce of shock and shock/vortex interactions which can make a significant difference to the vortex breakdown behavior and aerody-namic characteristic of the flying-wing configuration.Based on the experimental data of a low-as-pect-ratio common research model with a 65°swept flying-wing configuration and a 0.16 wing-body thickness ratio,through reducing the wing-body thickness while keeping the round leading edge and outer wing geometry identical,wing-body thickness effects on the aerodynamic and vor-tex flow characteristics of the flying-wing configuration in transonic flow field have been studied numerically methods.The investigation indicated that wing-body thickness ratio reduced model has a gentle change in vertex strength along chord-wise direction and the vortex strength is high-er than that of the original model before x/Cr =0.25,meanwhile it can delay vortex breakdown by an angle of 8°compared with the original model at Mach number 0.9.