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本文提出了一种旁侧进气翼身融合体布局一体化气动构型,并首次提出了一种基于双乘波体旋转对拼的前体设计方案.在全参数化构型设计的基础上,以数值模拟为评估手段,给定不同设计参数对前体进行了分析,结果表明在获得良好容积和升阻性能的同时,利用左右乘波面作为进气道的外压缩面,可保证进气道入口截面处具有较好的流场均匀性和来流捕获量.进而针对幂曲线、余弦曲线等4种典型的翼前缘形状,开展了整机数值分析.计算结果证明了飞行器的高升阻比优势,同时也发现由于机体/机翼的耦合作用,小攻角飞行状态下机翼前缘可以捕获机体压缩产生的部分高压,故在0°和4°攻角条件下,4种构型的升阻比呈现完全不同大小排列顺序.这一结果也为后续的优化设计提供了方向,即前缘形线的合理选择应可进一步提高飞行器的升阻比.
In this paper, an integrated aerodynamic configuration of the lateral airfoil fuselage fusion is proposed, and a precursor design scheme based on double-carrier wave rotation is proposed for the first time.Based on the design of fully parametric configuration , The numerical simulation is used as the assessment method, and given the different design parameters, the precursor is analyzed. The results show that using the left and right wave surfaces as the outer compression surface of the intake passage, while obtaining good volume and lift resistance performance, The cross section of the entrance has better flow field uniformity and flow trapping.According to four kinds of typical wing leading edge shapes, such as power curve and cosine curve, the whole machine numerical analysis is carried out.The calculation results show that the high lift resistance It is also found that due to the body / wing coupling, the leading edge of the wing can capture part of the high pressure generated by the compression of the fuselage during flight at small angles of attack. Therefore, at 0 ° and 4 ° angle of attack, the four configurations The ratio of lift to drag shows a completely different order of magnitude.This result also provides the direction for the subsequent optimization design, that is, the rational selection of the leading edge shape line should further improve the lift-drag ratio of the aircraft.