内锥流场参数对定平面形状乘波体性能的影响OA
Influence of internal conical flow field parameters on performance of planform-customized waveriders
通过求解Taylor-Maccoll方程结合特征线法,快速生成了具有不同物面边界的直激波内锥流场,实现了使用内锥流场的定平面形状乘波体设计.比较不同边界、压力分布的直激波流场性质,并以上反翼双后掠外形为基准平面形状设计定平面形状乘波体,分析不同内锥流场对定平面形状乘波体性能的影响.结果表明,当直激波内锥流场物面边界不同时,得到的定平面形状乘波体均具有较高的升阻比,而且激波位置非常接近,表现出良好的乘波特性;当物面边界由上扬变为下倾时,即沿物面压力由增大变为减小,下表面的压缩性也逐渐减弱,但总压恢复系数基本不变;另外,基准流场的物面边界越趋于直线,基准流场、所生成乘波体下表面的流场均匀性越好.
The straight-shock internal conical flow fields with various wall boundaries are generated by solving the Taylor-Maccoll equation combined with the method of characteristics.Employing the geometric relation in the osculating-cone method,the planform-customized waverider design is achieved using the straight-shock internal coni-cal flow fields.The properties of straight-shock flow fields with different boundaries and pressure distributions were compared.Taking the 3D leading edge of one double swept waverider with wing dihedral as the baseline planform shape,the planform-customized waveriders using the internal conical flow fields with different boundaries are de-signed.Then the effect of the internal flow fields on the waverider performance was analyzed.The results show that the planform-customized waveriders generated from the internal flows with different wall boundaries feature high lift-to-drag ratio.The shock wave positions in their flow fields are nearly identical,indicating promising wave-riding perfor-mance.When the wall boundaries of the basic internal flow fields vary from elevated to descent profile along the axial coordinate,the pressure of the lower surface transitions from increasing to decreasing.The compression ability under the lower surface also decreases,but the total pressure recovery coefficients remain similar.In addition,as the wall boundary approaches a straight line more closely,the flow field uniformity under the lower surface of waveriders is bet-ter,just like that of the basic internal flow fields.
孟旭飞;白鹏;刘传振
中国航天空气动力技术研究院,北京 100074中国航天空气动力技术研究院,北京 100074中国航天空气动力技术研究院,北京 100074
航空航天
乘波体定平面形状直激波内锥流场物面边界
waveridercustomized planformstraight shock waveinternal conical flow fieldwall boundary
《航空学报》 2026 (1)
90-102,13
国家自然科学基金(U22B20133,12272366) National Natural Science Foundation of China(U22B20133,12272366)
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