Aerodynamic performance of new conceptual configuration of high speed vehicle's heat flux and drag reduction

Shuai ZHANG

doi:10.13224/j.cnki.jasp.20200477

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Aerodynamic performance of new conceptual configuration of high speed vehicle's heat flux and drag reduction

Aerothermodynamics and Aeroengine Design | 更新时间：2025-04-07

- Aerodynamic performance of new conceptual configuration of high speed vehicle's heat flux and drag reduction
- Journal of Aerospace Power Vol. 36, Issue 11, Pages: 2292-2305(2021)
- 作者机构：
  
  中国航天科工集团有限公司北京空天技术研究所，北京 100074
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20200477
  CLC：
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Shuai ZHANG. Aerodynamic performance of new conceptual configuration of high speed vehicle's heat flux and drag reduction[J]. Journal of Aerospace Power, 2021, 36(11): 2292-2305.
DOI：

Shuai ZHANG. Aerodynamic performance of new conceptual configuration of high speed vehicle's heat flux and drag reduction[J]. Journal of Aerospace Power, 2021, 36(11): 2292-2305. DOI： 10.13224/j.cnki.jasp.20200477.

摘要

提出了一种高速飞行条件下兼具防热减阻的凹腔槽道气动构型，建立了凹腔深宽比为1，槽道高度分别为0、10、20、30、40 mm的凹腔槽道构型，以及槽道入口高度固定为30 mm，出口高度分别为35、40、45、50 mm的扩张型凹腔槽道构型。采用求解Navier⁃Stokes（N⁃S）方程方法进行计算，获得了不同算例的鼻锥外壁面热流密度分布以及构型阻力系数的变化情况，分析了凹腔槽道构型参数对气动热与气动力性能的影响。数值结果表明凹腔槽道构型能够达到预期的防热减阻效果。较优构型（槽道进出口高度比为30/50）的防热率与减阻率分别达到40.1%和16.8%。槽道高度越高，减阻效果越好，但防热效率降低。相较于平直型凹腔槽道，扩张型凹腔槽道构型能够在保证防热率不变的情况下显著提升减阻性能。

Abstract

A heat flux and drag reduction conceptual configuration combining the forward⁃facing cavity and the channel was proposed with high speed.The ength⁃to⁃depth ratio of forward⁃facing cavity was set as 1.The first series of channel height with 0

40 mm

and the second series of channel entrance height with

30 mm and channel exit height with 35

50 mm were taken into consideration.The wall heat flux distributions and drag coefficient were extracted from the flow field structures to evaluate the heat flux and drag reduction characteristics via solving Navier⁃Stokes （N⁃S） equations.The results showed that the cavity⁃channel configuration can achieve the expected heat flux and drag reduction.Compared with the baseline blunt cone

the cavity⁃channel configuration （the channel entrance height to exit height ratio of 30/50） had the optimal but not best heat flux and drag reduction performance within the range considered

and the heat flux and drag reduction rates reached approximately 40.1% and 16.8%

respectively.Higher channel height indicated better the drag reduction

but the heat flux protection effectiveness became weakened.Moreover

higher channel exit height

with a constant channel entrance height could enhance the drag reduction effectiveness without any heat flux reduction penalty.

关键词

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references

HUANG Wei . A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations [J]. Journal of Zhejiang University:Science A Applied Physics and Engineering , 2015 , 16 （ 7 ）: 551 ⁃ 561 .

WANG Zhenguo , SUN Xiwan , HUANG Wei , et al . Experimental investigation on drag and heat flux reduction in supersonic/hypersonic flows:a survey [J]. Acta Astronautica , 2016 , 129 : 95 ⁃ 110 .

LI Shibin , WANG Zhenguo , HUANG Wei , et al . Analysis of flowfield characteristics for equal polygon opposing jet on different freeflow conditions [J]. Acta Astronautica , 2017 , 133 : 50 ⁃ 62 .

GERDROODBARY M B , FALLAH K , POURMIRZAAGHA H . Characteristics of transverse hydrogen jet in presence of multi air jets within scramjet combustor [J]. Acta Astronautica , 2017 , 132 : 25 ⁃ 32 .

ZHANG Ruirui , HUANG Wei , LI Langquan , et al . Drag and heat flux reduction induced by the pulsed counterflowing jet with different periods on a blunt body in supersonic flows [J]. International Journal of Heat and Mass Transfer , 2018 , 127 : 503 ⁃ 512 .

ZHANG Ruirui , HUANG Wei , YAN Li , et al . Drag and heat flux reduction induced by the pulsed counterflowing jet with different waveforms on a blunt body in supersonic flows [J]. Acta Astronautica , 2019 , 160 : 635 ⁃ 645 .

DONG Hao , DENG Fan , XIE Feng , et al . Drag reduction effect for hypersonic lifting⁃body vehicle with counterflowing jet [J]. Transactions of Nanjing University of Aeronautics and Astronautics , 2018 , 35 （ 5 ）: 789 ⁃ 799 .

RONG Yisheng . Drag reduction research in supersonic flow with opposing jet [J]. Acta Astronautica , 2013 , 91 : 1 ⁃ 7 .

DASO E O , PRITCHETT V E , WANG T S , et al . The dynamics of shock dispersion and interactions in supersonic freestreams with counterflowing jets [R]. AIAA⁃2007⁃1423 , 2007 .

GERDROODBARY M B , BISHEHSARI S , HOSSEINALIPOUR S M , et al . Transient analysis of counterflowing jet over highly blunt cone in hypersonic flow [J]. Acta Astronautica , 2012 , 73 : 38 ⁃ 48 .

SATHEESH K , REDDY K , JAGADEESH G . Concentrated electrical energy deposition can reduce the wave drag around blunt bodies flying at hypersonic Mach number [J]. Physical Review:B , 2006 , 57 （ 20 ）: 13235 ⁃ 13240 .

GANESH A M , JOHN B . Concentrated energy addition for active drag reduction in hypersonic flow regime [J]. Acta Astronautica , 2018 , 142 : 221 ⁃ 231 .

SATHEESH K , JAGADEESH G . Effect of concentrated energy deposition on the aerodynamic drag of a blunt body in hypersonic flow [J]. Physics of Fluids , 2007 , 19 （ 3 ）: 31701 .1⁃31701. 4 .

BIBIN J , VINAYAK K . Investigation of energy deposition technique for drag reduction at hypersonic speeds [J]. Applied Mechanics and Materials , 2013 , 367 : 222 ⁃ 227 .

TAGUCHI S , OHNISHI N , FURUDATE M , et al . Numerical analysis of drag reduction for supersonic blunt body by pulse energy deposition [R]. AIAA⁃2007⁃1235 ， 2007 .

SPERBER D , ECKEL H A , STEIMER S , et al . Objectives of laser⁃induced energy deposition for active flow control [J]. Contributions to Plasma Physics , 2012 , 52 （ 7 ）: 636 ⁃ 643 .

JOARDER R . On the mechanism of wave drag reduction by concentrated laser energy deposition in supersonic flows over a blunt body [J]. Shock Waves , 2019 ， 29 （ 4 ）: 487 ⁃ 497 .

KALIMUTHU R , RATHAKRISHNAN E . Aerospike for drag reduction in hypersonic flow [R]. AIAA⁃2008⁃4707 ， 2008 .

YADAV R , GUVEN U . Aerothermodynamics of a hypersonic projectile with a double⁃disk aerospike [J]. Aeronautical Journal , 2013 , 117 （ 1195 ）: 913 ⁃ 928 .

YADAV R , VELIDI G , GUVEN U . Aerothermodynamics of generic re⁃entry vehicle with a series of aerospikes at nose [J]. Acta Astronautica , 2014 , 96 : 1 ⁃ 10 .

HUANG Wei , LI Langquan , YAN Li , et al . Drag and heat flux reduction mechanism of blunted cone with aerodisks [J]. Acta Astronautica , 2017 , 138 : 168 ⁃ 175 .

SAHOO D , DAS S , KUMAR P , et al . Effect of spike on steady and unsteady flow over a blunt body at supersonic speed [J]. Acta Astronautica , 2016 , 128 : 521 ⁃ 533 .

KULKARNI V , MENEZES V , REDDY K . Effectiveness of aerospike for drag reduction on a blunt cone in hypersonic flow [J]. Journal of Spacecraft and Rockets , 2010 , 47 （ 3 ）: 542 ‑ 544 .

ESFEH M K , TAJALLI S M , LIU P . Evaluation of aerospike for drag reduction on a blunt nose using experimental and numerical modeling [J]. Acta Astronautica , 2019 , 160 : 656 ‑ 671 .

WYSOCKI O , SCHÜLEIN E , SCHNEPF C . Experimental study on wave drag reduction at slender bodies by a self⁃aligning aerospike [J]. Notes on Numerical Fluid Mechanics and Multidisciplinary Design , 2014 , 124 : 583 ⁃ 590 .

GERDROODBARY M B , HOSSEINALIPOUR S M . Numerical simulation of hypersonic flow over highly blunted cones with spike [J]. Acta Astronautica , 2010 , 67 （ 1/2 ）: 180 ‑ 193 .

PISH F , MORADI R , EDALATPOUR A , et al . The effect of coolant injection from the tip of spike on aerodynamic heating of nose cone at supersonic flow [J]. Acta Astronautica , 2019 , 154 : 52 ⁃ 60 .

OU Min , YAN Li , HUANG Wei , et al . Design exploration of combinational spike and opposing jet concept in hypersonic flows based on CFD calculation and surrogate model [J]. Acta Astronautica , 2019 , 155 : 287 ⁃ 301 .

ZHANG Ruirui , DONG Minzhou , HUANG Wei , et al . Drag and heat flux reduction mechanism induced by the combinational forward⁃facing cavity and pulsed counterflowing jet configuration in supersonic flows [J]. Acta Astronautica , 2019 , 160 : 62 ⁃ 75 .

HUANG Wei , CHEN Zheng , YAN Li , et al . Drag and heat flux reduction mechanism induced by the spike and its combinations in supersonic flows:a review [J]. Progress in Aerospace Sciences , 2019 , 105 : 31 ⁃ 39 .

HUANG Wei , YAN Li , LIU Jun , et al . Drag and heat reduction mechanism in the combinational opposing jet and acoustic cavity concept for hypersonic vehicles [J]. Aerospace Science and Technology , 2015 , 42 : 407 ⁃ 414 .

HUANG Wei , LIU Jun , XIA Zhixun . Drag reduction mechanism induced by a combinational opposing jet and spike concept in supersonic flows [J]. Acta Astronautica , 2015 , 115 : 24 ‑ 31 .

HUANG Wei , JIANG Yanping , YAN Li , et al . Heat flux reduction mechanism induced by a combinational opposing jet and cavity concept in supersonic flows [J]. Acta Astronautica , 2016 , 121 : 164 ⁃ 171 .

SUN Xiwan , HUANG Wei , GUO Zhenyun , et al . Multiobjective design optimization of hypersonic combinational novel cavity and opposing jet concept [J]. Journal of Spacecraft and Rockets , 2017 , 54 （ 3 ）: 662 ⁃ 671 .

GERDROODBARY M B . Numerical analysis on cooling performance of counterflowing jet over aerodisked blunt body [J]. Shock Waves , 2014 , 24 （ 5 ）: 537 ⁃ 543 .

ZHANG Ruirui , HUANG Wei , YAN Li , et al . Numerical investigation of drag and heat flux reduction mechanism of the pulsed counterflowing jet on a blunt body in supersonic flows [J]. Acta Astronautica , 2018 , 146 : 123 ⁃ 133 .

HARTMANN J . On a new method for the generation of sound⁃waves [J]. Physical Review Journals Archive , 1922 , 20 （ 6 ）: 719 ⁃ 727 .

BURBANK P B , STALLINGS R L . Heat⁃transfer and pressure measurements on a flat⁃face cylinder at a Mach number range of 2.49 to 4.44 [R]. NASA⁃TM⁃X⁃19 , 1959 .

YUCEIL B , DOLLING D , WILSON D . A preliminary investigation of the Helmholtz resonator concept for heat flux reduction [R]. AIAA⁃1993⁃2742 , 1993 .

SILTON S I , GOLDSTEIN D B . Ablation onset in unsteady hypersonic flow about nose tip with cavity [J]. Journal of Thermophysics and Heat Transfer , 2000 , 14 （ 3 ）: 421 ⁃ 434 .

SEILER F , SRULIJES J , PASTOR M G , et al . Heat fluxes inside a cavity placed at the nose of a projectile measured in a shock tunnel at Mach 4.5 [J]. Notes on Numerical Fluid Mechanics and Multidisciplinary Design , 2008 , 96 : 309 ⁃ 316 .

SELVARAJ S , GOPALAN J , REDDY K . Investigation of missile⁃shaped body with forward⁃facing cavity at Mach 8 [J]. Journal of Spacecraft and Rockets , 2009 , 46 （ 3 ）: 577 ⁃ 591 .

GUPTA A , RUFFIN S , NEWFIELD M , et al . Aerothermodynamic performance enhancement and design of sphere⁃cones using the artificially blunted leading edge concept [R]. AIAA⁃1999⁃897 , 1999 .

ANAZADEHSAYED A , GERDROODBARY M B , AMINI Y , et al . Mixing augmentation of transverse hydrogen jet by injection of micro air jets in supersonic crossflow [J]. Acta Astronautica , 2017 , 137 : 403 ⁃ 414 .

LI Junzhe , YAN Chao , KE Lun , et al . Research on scheme effect of computational fluid dynamics in aerothermal [J]. Journal of Beijing University of Aeronautics and Astronautics , 2003 , 29 （ 11 ）: 1022 ⁃ 1025 .

PAN Jing , YAN Chao , GENG Yunfei . Aerothermodynamic of the waveriders applying artificially blunted leading edge concept [R]. AIAA⁃2009⁃748 , 2009 .

SUN Xiwan , HUANG Wei , OU Min , et al . A survey on numerical simulations of drag and heat reduction mechanism in supersonic/hypersonic flows [J]. Chinese Journal of Aeronautics , 2019 , 32 （ 4 ）: 771 ⁃ 784 .

ENGBLOM W A , GOLDSTEIN D B , LADOON D , et al . Fluid dynamics of hypersonic forward⁃facing cavity flow [J]. Journal of Spacecraft and Rockets , 1997 , 34 （ 4 ）: 437 ⁃ 444 .

ENGBLOM W A , YUCEIL B , GOLDSTEIN D B , et al . Experimental and numerical study of hypersonic forward⁃facing cavity flow [J]. Journal of Spacecraft and Rockets , 1996 , 33 （ 3 ）: 353 ⁃ 359 .

张帅 , 方蜀州 , 郭建 . 头部钝化的无翼航天器气动性能研究 [J]. 飞行力学 , 2020 , 38 （ 6 ）: 56 ⁃ 62,69 .

ZHANG Shuai , FANG Shuzhou , GUO Jian . Study on aerodynamic performance of wingless spacecraft with head blunted [J]. Flight Dyanmics , 2020 , 38 （ 6 ）: 56 ⁃ 62,69 . （in Chinese）

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