摘要
基于二元混压式高超声速进气道和密切锥乘波体,设计了一腹部并列进气的高超声速乘波前体/进气道一体化前体模型,并数值模拟研究了该模型在不同飞行马赫数和攻角下的气动特性。计算结果表明:设计的一体化前体模型很好地结合了二元高超声速进气道和乘波体流场结构特点,乘波前体结构可为进气道提供均匀的进口流场,且进气道性能基本保持不变;一体化前体模型在低于设计点马赫数和正攻角飞行状态下仍具有良好的飞行性能,但在负攻角飞行姿态时,随着攻角角度的增大一体化前体模型的升阻特性和进气特性均快速恶化。
Based on the 2D mixed compression hypersonic inlet and osculating waverider design methods,an integrated hypersonic vehicle forebody has been designed, in which two inlets parallel were mounted un.der the fuselage. The integrated model flowfield under different flying Mach numbers and attack angles hasbeen studied using CFD simulation. The numerical simulation results show that the integrated design meth.od can couple the flowfields of the inlet and waverider well. The waverider forebody can provide uniformflowfield for the inlet, and the inlet performance remains essentially unchanged. Under the low flying Machnumber, the integrated model also has good performance. With the positive angles of attack, the lift dragand intake characteristics of the forebody are still good, but for the negative angles of attack, with the angleincreasing, the characteristics get worse quickly.
出处
《燃气涡轮试验与研究》
北大核心
2018年第1期13-17,23,共6页
Gas Turbine Experiment and Research
