最小波阻锥导乘波体和三维内转式进气道一体化设计

贺旭照; 卫锋; 刘福军; 陈圣兵

doi:10.7638/kqdlxxb-2021.0375

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最小波阻锥导乘波体和三维内转式进气道一体化设计

专栏——内外流一体化技术 | 更新时间：2026-05-28

- 最小波阻锥导乘波体和三维内转式进气道一体化设计
- Integrated design of minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets
- 空气动力学学报 2022年40卷第1期页码：77-83
- 作者机构：
  
  1. 北京流体动力科学研究中心,北京,100120
  2. 中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,绵阳,621000
- 作者简介：
  
  贺旭照（1977-），男，陕西蒲城人，研究员，研究方向：高超声速机体推进一体化技术. E-mail：2233475937@qq.com
  陈圣兵*（1984-），男，湖北宜昌人，副研究员，研究方向：高超飞行器技术. E-mail：nudt_chen@163.com
- 基金信息：
  
  国家自然科学基金（51376192，91216303）
- DOI：10.7638/kqdlxxb-2021.0375
  中图分类号： V221
- 纸质出版：2022
- 稿件说明：
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贺旭照, 卫锋, 刘福军, 等. 最小波阻锥导乘波体和三维内转式进气道一体化设计[J]. 空气动力学学报, 2022, 40(1): 77−83.

HE Xuzhao, WEI Feng, LIU Fujun, et al. Integrated design of minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets[J]. 2022, 40(1): 77-83.
贺旭照, 卫锋, 刘福军, 等. 最小波阻锥导乘波体和三维内转式进气道一体化设计[J]. 空气动力学学报, 2022, 40(1): 77−83. DOI： 10.7638/kqdlxxb-2021.0375

HE Xuzhao, WEI Feng, LIU Fujun, et al. Integrated design of minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets[J]. 2022, 40(1): 77-83. DOI： 10.7638/kqdlxxb-2021.0375.

摘要

发展了最小波阻锥导乘波体和三维内转式进气道的一体化乘波体进气道设计新方法，给出了一个设计实例，评估了新型一体化前体进气道在典型状态下的流场结构和性能，验证了设计方法的正确性。文中首先介绍并验证了基于最小阻力理论或其他优化方法的最小波阻锥导乘波体的设计方法，然后介绍了内锥基准流场的设计过程，进一步介绍了流线追踪三维内转式进气道同最小波阻锥导乘波体的一体化设计方法，并对一体化构型在设计状态下的流场结构和流动参数进行了分析评估，结果符合预期。最后评估了新型一体化前体进气道在非设计条件下的性能，结果显示其具有较高的压缩进气效率。这种新型最小波阻锥导乘波体和三维内转式进气道的一体化设计技术，丰富了吸气式高超飞行器的一体化布局方案，可为后续吸气式高超飞行器一体化布局提供设计方法支撑。

Abstract

This paper develops an integrated design methodology for minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets. To verify its feasibility

flow fields and compression characteristics of a novel integrated forebody inlet designed by this method are evaluated at typical flying conditions. Firstly

the design method for minimal wave drag cone-derived waveriders is introduced and verified. Then the flow fields around the inward turning cone and the integrated design method of a minimal drag cone-derived waverider with a three-dimensional inward turning inlet is demonstrated. The flow-field structures and parameters of the integrated waverider inlet at design conditions are examined in detail. The results agree well with the design expectations. Finally

the performance of the inlet of the integrated waverider at off design conditions are investigated by Computational Fluid Dynamic. The results show that the novel integrated waverider forebody inlet has desirable flow compression performance. This novel integration design method for minimal wave drag conic waveriders with there-dimensional inward turning inlet provides an alternative choice for the configuration integration of airbreathing hypersonic vehicles.

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references

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