高超声速翼型气动特性设计与研究

Aerodynamic characteristics design of hypersonic airfoil

具有更宽速度域的优良的气动特性已经成为高超声速飞行器发展的必然趋势。因此,对于现代高超声速飞行器翼型的设计,需考虑宽速度域范围内的气动特性。采用基于RANS的CFD数值计算方法,开展了高超声速翼型的气动特性设计与研究,设计了两种具有更加优良的低速、跨声速气动特性的高超声速翼型。对这两种翼型进行了综合评估,并与基准翼型的气动力特性进行对比分析。研究结果表明,第一种优化翼型在跨声速状态下的升阻比达到97. 40,第二种优化翼型在低速状态下的最大升力达到0. 719,相比于基准翼型,两种优化翼型在低速和跨声速下的气动特性得到提高。

Aerodynamic characteristics in a wide velocity range should be considered in the design of modern hypersonic aircraft airfoils. The aerodynamic characteristics of hypersonic airfoils were designed and studied by using the CFD numerical method based on RANS. Two kinds of hypersonic airfoils with better low - speed and transonic aerodynamic characteristics were designed. The two airfoils were evaluated and compared with the reference airfoil. The results showed that the lift - drag ratio of the first optimized airfoil at transonic speed is 97.40, and the maxinmm lift of the second optimized airfoil at low speed is 0. 719. Compared with the reference airfoil, the aerodynamic characteristics of the two optimized airfoils at low speed and transonic speed are improved.