Integrated design of minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets

HE Xuzhao; WEI Feng; LIU Fujun; CHEN Shengbing

doi:10.7638/kqdlxxb-2021.0375

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Integrated design of minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets

更新时间：2026-05-28

- Integrated design of minimal wave drag cone-derived waveriders and three-dimensional inward turning inlets
- Vol. 40, Issue 1, Pages: 77-83(2022)
- 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：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0375
  CLC： V221
- Published：2022
- 稿件说明：
移动端阅览
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.

关键词

Keywords

references

HANEY J, BEAULIEU W. Waverider inlet integration issues[C]//32nd Aerospace Sciences Meeting and Exhibit, Reno, NV, USA. Reston, Virigina: AIAA, 1994. AIAA 1994-0383. doi: 10.2514/6.1994-383

SHUKLA V, GELSEY A, SCHWABACHER M, et al. Automated design optimization for the P2 and P8 hypersonic inlets[J]. Journal of Aircraft, 1997, 34(2): 228-235. DOI:10.2514/2.2161

BERENS T M, BISSINGER N C. Forebody precompression effects and inlet entry conditions for hypersonic vehicles[J]. Journal of Spacecraft and Rockets, 1998, 35(1): 30-36. DOI:10.2514/3.26994

BILLIG F, BAURLE R, TAM C J, et al. Design and analysis of streamline traced hypersonic inlets[C]//9th International Space Planes and Hypersonic Systems and Technologies Conference, Norfolk, VA, USA. Reston, Virigina: AIAA, 1999. AIAA 1999-4974. doi: 10.2514/6.1999-4974

SMART M K. Design of three-dimensional hypersonic inlets with rectangular-to-elliptical shape transition[J]. Journal of Propulsion and Power, 1999, 15(3): 408-416. DOI:10.2514/2.5459

O'NEILL M K L, LEWIS M J. Optimized scramjet integration on a waverider[J]. Journal of Aircraft, 1992, 29(6): 1114-1121. DOI:10.2514/3.56866

TAKASHIMA N, LEWIS M. Engine-airframe integration on osculating cone waverider-based vehicle designs[C]//32nd Joint Propulsion Conference and Exhibit, Lake Buena Vista, FL. Reston, Virginia: AIAA, 1996.doi: 10.2514/6.1996-2551

O’BRIEN T F, LEWIS M J. Rocket-based combined-cycle engine integration on an osculating cone waverider vehicle[J]. Journal of Aircraft, 2001, 38(6): 1117-1123. DOI:10.2514/2.2880

SOBIECZKY H, DOUGHERTY F C, JONES K. Hypersonic waverider design from given shock waves[C ] //1rst International Hypersonic Waverider Symposium, University of Maryland, USA, 1990. https://www.researchgate.net/publication/225015124_Hypersonic_Waverider_Design_from_Given_Shock_Waves

STARKEY R P, LEWIS M J. Design of an engine-airframe integrated hypersonic missile within fixed box constraints[C]//37th Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 1999. AIAA 99-0509. doi: 10.2514/6.1999-509

YOU Y C, ZHU C X, GUO J L. Dual waverider concept for the integration of hypersonic inward-turning inlet and airframe forebody[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany. Reston, Virginia: AIAA, 2009. doi: 10.2514/6.2009-7421

LI Y Q, AN P, PAN C J, et al. Integration methodology for waverider-derived hypersonic inlet and vehicle forebody[C]//19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Atlanta, GA. Reston, Virginia: AIAA, 2014.doi: 10.2514/6.2014-3229

HE X Z, ZHOU Z, NI H L. Integrated design methods and performance analyses of osculating inward turning cone waverider forebody inlet(OICWI)[J]. Journal of Propulsion Technology, 2012, 33(4): 510-515. (in Chinese)

HE X Z, LE J L, ZHOU Z, et al. Osculating inward turning cone waverider/inlet (OICWI) design methods and experimental study[C]//Proc of the 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, Tours, France. Reston, Virginia: AIAA, 2012. doi: 10.2514/6.2012-5810

TAYLOR T, VANWIE D. Performance analysis of hypersonic shape-changing inlets derived from morphing streamline traced flowpaths[C]//15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, Ohio. Reston, Virginia: AIAA, 2008. doi: 10.2514/6.2008-2635

MOEREL J L, VERAAR R, HALSWIJK W H C, et al. Internal flow characteristics of a rectangular ramjet air intake[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, Denver, Colorado. Reston, Virginia: AIAA, 2009. doi: 10.2514/6.2009-5076

GOONKO Y P, MAZHUL I I, MARKELOV G N. Convergent-flow-derived waveriders[J]. Journal of Aircraft, 2000, 37(4): 647-654. DOI:10.2514/2.2647

NONWEILER T R F. Aerodynamic problems of manned space vehicles[J]. The Journal of the Royal Aeronautical Society, 1959, 63(585): 521-528. DOI:10.1017/s0368393100071662

HE X Z, LE J L, WU Y C. Design of a curved cone derived waverider forebody[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany. Reston, Virginia: AIAA, 2009. doi: 10.2514/6.2009-7423

HARDER K C, RENNEMANN JR C. On boattail bodies of revolution having minimum wave drag[R ] . NACA-TR-1271, NACA-TN-3478, 1955. https://ntrs.nasa.gov/api/citations/19930084271/downloads/19930084271.pdf

ZUCRCW M J, HOFFMAN J D. Gas dynamics, volume II[M]. John Wiley Sons, London. 1977: 112-266. doi: 10.1017/S0001924000094884

HE X Z, ZHAO H Y, LE J L. Application of wall function boundary condition considering heat transfer and compressibility[J]. Acta Aerodynamica Sinica, 2006, 24(4): 450-453. (in Chinese)

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Design of continuous streamline tracing waverider forebody inlet

Rotating detonation propulsion technology for high-speed aircrafts

Prediction of aerodynamic characteristics of hypersonic vehicle by improved k-ω-γ transition model

Aerodynamic prediction for waveriders using deep residual learning

Numerical simulation on gust responses of high aspect ratio aircraft

Related Author

WU Yingchuan

HE Yuanyuan

WEI Feng

YU Anyuan

SHI Yingchen

ZHANG Renshuai

JI Zifei

WANG Bing

Related Institution

School of Aerospace Engineering, Tsinghua University, Beijing

Shenyang Engine Research Institute, AECC, Shenyang

Research Institute for Rural Electrification of Ministry of Water Resources, Hangzhou

Beijing Institute of Technology, Beijing

China Academy of Aerospace Aerodynamics

AI问答

⁰