CAJ | 학술논문

以二元高超声速进气道为研究对象,以数值模拟为手段,详细分析了该进气道内壁面上的压差阻力、摩擦阻力、总阻力随飞行马赫数的变化.接着用流线跟踪得到该二元高超声速进气道的分流面,研究了作用在该分流面上的附加阻力随飞行马赫数的变化.为了更准确地评价该进气道的阻力特性,采用了进气道的推力效率和推阻比两个概念,并且探讨了它们随飞行马赫数的变化.最后,分析讨论了作用在该进气道捕获流管上的实际总阻力随飞行马赫数的变化.
이이원고초성속진기도위연구대상,이수치모의위수단,상세분석료해진기도내벽면상적압차조력、마찰조력、총조력수비행마혁수적변화.접착용류선근종득도해이원고초성속진기도적분류면,연구료작용재해분류면상적부가조력수비행마혁수적변화.위료경준학지평개해진기도적조력특성,채용료진기도적추력효솔화추조비량개개념,병차탐토료타문수비행마혁수적변화.최후,분석토론료작용재해진기도포획류관상적실제총조력수비행마혁수적변화.
A detailed Analysis and investigation is performed in the text on the variation of the pressure drag and friction drag and total drags on the internal walls of the two-dimensional hypersonic inlet along with the variation of Mach numbers . Besides, the variation of additive drags acted on the distributary surface gained by stream traced method along with the variation of Mach numbers are particularly studied. In order to evaluate drags trait of the two-dimensional hypersonic inlet, Thrust efficiency and Thrust / drag ratio are used and their variation along with the variation of Mach number was also particularly analyzed and investiga-ted. At last, the variation of the total drags acted on the captured flow tube along with the variation of Mach numbers are aslo detailedly analyzed and investigated.