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Aerodynamic characteristics of waverider and its integrated configuration with blunt leading edge
Authors
王发民
陈雪冬
Publication date
1 February 2013
Publisher
Abstract
以最大升阻比为优化目标,在锥型流场中优化设计出乘波布局,并考虑高超声速飞行器的防热需求,对乘波布局进行钝化设计,利用数值模拟和风洞实验两种手段,研究钝化前缘乘波布局的气动特性.结果表明:在一定钝化半径内,随着钝化半径的增加,乘波构型的升力特性变化仅为2%,但阻力特性增加近3倍,升阻比降低了将近50%.尽管如此,为了钝化乘波布局,仍维持了较高的升阻比,升阻比为3左右.同时,以二维顶压式进气道为基础,在多级楔锥组合体流场中,设计出满足超燃发动机进气要求的乘波前体/进气道一体化构型,并进行前缘钝化设计.针对一体化构型进行了数值验证,结果表明:此类一体化构型升阻比大于2.6,同时发动机总压恢系复数保持在40%左右,满足进气道的要求
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Institute Of Mechanics,Chinese Academy of Sciences
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Last time updated on 12/02/2018