典型二元高超声速进气道设计方法研究

张晓嘉; 梁德旺; 李博; 袁化成

典型二元高超声速进气道设计方法研究

南京航空航天大学内流研究中心, 南京 210016

基金项目: 国家863高技术研究发展计划(2004AA723020)资助项目

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出版历程
- 收稿日期: 2006-08-08
- 修回日期: 2007-03-15
- 刊出日期: 2007-08-28

Study of design method of typical two-dimensional hypeisonic inlet

Internal Fluid Flow Center, Nanjing Universty of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 综合了一系列典型二元高超声速进气道的设计和性能估算方法, 给出了可行的设计原则.在满足流量、增压以及工作范围(起动性能和反压承受能力)的条件下, 给出了进气道进口、外压波系、内压缩通道、唇罩及隔离段的设计方法.采用此方法, 以H=22800 m、Ma0=6为设计点, 完成了一高超声速进气道的初步设计, 并估算得到了进气道性能参数、进气道的起动马赫数和反压承受能力, 对比CFD计算结果, 误差不大.通过该方法得到的进气道具有结构简单、流量系数大、压缩损失小的特点, 不通过优化即可得到性能较为良好的模型.
- 航空、航天推进系统 /
- 高超声速进气道 /
- 设计 /
- 估算 /
- 外压波系 /
- 内压缩通道 /
- 隔离段
Abstract: A feasible design principle was developed by combining a series of design and performance predicting methods of typical two-dimensional hypersonic inlets.The design methods of inlet entrance, external compression shocks, internal contraction tunnel, cowl and isolator were presented at the given flux, pressure rise ratio and working range(starting Mach number and capability of enduring back pressure).A preliminary design of hypersonic inlet at the design point of H=22 800 m, Ma0=6 was conducted, so the performance parameters(pressure rise ratio, Mach number, temperature rise ratio and total pressure recovery), starting Mach number and capability of enduring back pressure were predicted and calculated with small error.With this method, the inlet could present simple construction, high flow coefficient and low compression loss in developing a satisfactory model without optimization.
- aerospace propulsion system /
- hypersonic inlet /
- design /
- predict /
- external compression shocks /
- internal contraction tunnel /
- isolator

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参考文献(18)

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