密切曲面锥导乘波体的设计与理论分析

doi:10.13675/j.cnki.tjjs.190418

推进技术 ›› 2021, Vol. 42 ›› Issue (2): 298-308.DOI: 10.13675/j.cnki.tjjs.190418

密切曲面锥导乘波体的设计与理论分析

卫锋，丁国昊，马志成，贺旭照

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，四川绵阳 621000

出版日期:2021-02-02 发布日期:2021-08-15
作者简介:卫锋，硕士，助理研究员，研究领域为高速飞行器气动布局理论和应用。E-mail：wf_nudt@hotmail.com

Design and Theoretical Analysis of Osculating Curve Cone Derived Wave-Rider

Science and Technology on Scramjet Laboratory CARDC，Mianyang 621000，China

Online:2021-02-02 Published:2021-08-15

摘要/Abstract

摘要： 将密切锥导乘波体技术应用于一般曲面锥流场，以期获得升阻比、容积率更高的密切曲面锥导乘波体。首先，设定不同乘波体后缘激波型线，在两种代表性曲面锥流场内，生成了四种乘波体构型，利用数值方法验证乘波体设计方法可行性；然后构造了三类典型单一控制变量的曲面锥流场，对比分析了对应密切曲面锥导乘波体性能变化规律。研究表明：（1）密切曲面锥导乘波体流面压力分布、后缘激波型线与理论设计吻合，关键位置压力与理论值相对偏差约1%，说明利用密切技术在曲面锥流场中“截取”乘波体的方法是可行的。（2）曲面锥流场控制参数不同，可获得升阻系数、容积率、压缩量增加，升阻比降低的乘波体，也可获得升阻比、容积率增加，升阻系数降低的乘波体。

关键词: 乘波体;密切技术;流场;理论分析;数值模拟

Abstract: In this paper， the osculating flowfield method was extended into general curve cone flow-field expects to get waveriders with higher lift to drag ratio and plot ratio. Under different constraint conditions of assumed shock trace （AST）， four typical wave-rider configurations were obtained in two typical curve cone flow-field. The feasibility verification and effectiveness analysis of this method have been studied by numerical ways. Three kinds of single parameter varying curve cone flow-field were constructed to analysis the performance variation law of osculating curve cone derived （OCC） wave-rider. The results showed that：（1） The pressure contours of wave-rider configurations at compression surface and exit plane， the assumed shock trace（AST）derived from MOC theory and numerical simulation were in good agreement with each other， and the pressure deviation could be controlled within 1%. （2）While the curve cone flow-field parameters were varying， wave-riders with increased in lift and drag coefficient， plot ratio， compression， and with decreased in lift to drag ratio could be derived. Also， wave-riders with increased in lift to drag ratio， plot ratio， and with decreased in lift and drag coefficient could be derived.

Key words: Wave-rider;Osculating method;Flow field;Theoretical analysis;Numerical simulations

卫锋，丁国昊，马志成，贺旭照. 密切曲面锥导乘波体的设计与理论分析[J]. 推进技术, 2021, 42(2): 298-308.

WEI Feng, DING Guo-hao, MA Zhi-cheng, HE Xu-zhao. Design and Theoretical Analysis of Osculating Curve Cone Derived Wave-Rider[J]. Journal of Propulsion Technology, 2021, 42(2): 298-308.

参考文献

[1] Lunan D. Wave-Rider， a Revised Chronology［R］. AIAA 2015-3529.
[2] Nonweiler T R F. Aerodynamic Problems of Manned Space Vehicles［J］. Journal of the Royal Aeronautical Society， 1959， 63： 521-528.
[3] Jones J G ， Moore K C， Pike J， et al. A Method for Designing Lifting Configurations for High Supersonic Speeds， Using Axisymmetric Flow Fields［J］. Ingenieur-Archiv， 1968， 37： 56-72.
[4] Corda S. Viscous Optimized Hypersonic Wave-Rider Designed from Flows over Cones and Minimum Drag Bodies［D］. College Park： University of Maryland， 1988.
[5] Mangin B， Benay R， Chanetz B， et al. Optimization of Viscous Wave-Riders Derived from Axisymmetric Power-Law Blunt Body Flows［J］. Journal of Spacecraft and Rockets， 2006， 43（5）： 990-998.
[6] Sobiezczky H， Dougherty F C， Jones K. Hypersonic Wave-Rider Design from Given Shock Waves［C］. College Park： First International Wave-Rider Symposium， 1990.
[7] Chauffour M L， Lewis M J. Corrected Wave-Rider Design for Inlet Applications［R］. AIAA 2004-0511.
[8] Chauffour M L. Shock-Based Wave-Rider Design with Pressure Corrections and Computational Simulations［D］. College Park： University of Maryland， 2004.
[9] Lewis M J， Chauffour M L. Shock-Based Wave-Rider Designed with Pressure Gradient Corrections and Computational Simulations［J］. Journal of Aircraft， 2005， 42（5）： 1350-1352.
[10] Patrick E Rodi. The Osculating Flow-Field Method of Wave-Rider Geometry［R］. AIAA 2005-0511.
[11] 贺旭照，倪鸿礼. 密切曲面锥乘波体-设计方法及性能分析［J］. 力学学报， 2011， 43（6）： 1077-1082.
[12] 贺旭照，周正，倪鸿礼. 密切内锥乘波前体进气道一体化设计和性能分析［J］. 推进技术， 2012， 33（4）：510-515.
[13] 贺旭照，乐嘉陵. 曲外锥乘波体进气道实用构型设计和性能分析［J］. 航空学报， 2017， 38（6）.
[14] Zucrow M J， Hoffman J D. Gas Dynamics Volume （п）［M］. New York： Library of Congress Cataloging， American， 1976.
[15] 卫锋，贺旭照，贺元元，等. 三维内转式进气道双激波基准流场的设计方法［J］. 推进技术， 2015， 36（3）： 358-364.
[16] 卫锋. 基于特征线理论的流线追踪内转向进气道设计方法研究［D］. 长沙：国防科学技术大学， 2012： 65-70.
[17] Nielsen J N. Missile Aerodynamics［M］. New York： McGraw-Hill Book Co. Inc.， 1960： 280-293.
[18] 卫锋，贺旭照，秦思，等. 密切弯曲激波乘波体技术的应用及有效性分析［J］. 推进技术， 2018， 39（2）： 277-285.

密切曲面锥导乘波体的设计与理论分析

Design and Theoretical Analysis of Osculating Curve Cone Derived Wave-Rider

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价