CAJ | 학술논문

为改善飞行器的升阻特性，提高其机动性能，利用数值仿真技术对稳定射流在超临界翼型的作用效果进行研究。通过动量系数变化对环量控制作用效果影响规律的研究分析后发现：稳定射流环量控制与无射流情况对比，有较强的优越性，在小迎角或负迎角就可以产生较大的升力。通过对后缘半径和射流口高度的变化对环量控制作用效果影响规律的研究分析，得到圆形后缘超临界环量控制翼型的初步设计方法。计算结果可为进一步研究环量控制对飞行器的影响奠定理论基础。
위개선비행기적승조특성，제고기궤동성능，이용수치방진기술대은정사류재초림계익형적작용효과진행연구。통과동량계수변화대배량공제작용효과영향규률적연구분석후발현：은정사류배량공제여무사류정황대비，유교강적우월성，재소영각혹부영각취가이산생교대적승력。통과대후연반경화사류구고도적변화대배량공제작용효과영향규률적연구분석，득도원형후연초림계배량공제익형적초보설계방법。계산결과가위진일보연구배량공제대비행기적영향전정이론기출。
In order to improve aircraft′s lift-drag characteristics and motor performance ,through the nu-merical simulation technology , effect of circulation control by steady jet on supercritical airfoil is re-searched .Through researching and analyzing the influent law of circulation control effect by changing the momentum coefficient , the results show that compared with the no blowing , the circulation control by steady jet is much better ,a larger lift can be obtained at a lower or negative attack angle .Through researc-hing and analyzing the influent law of circulation control effect by changing the trailing edge radius and height of jet slot ,the preliminary design method of supercritical airfoil on round edge is obtained .The cal-culation results can be used as theoretical basis of further research work of circulation control effect on aircraft.