Drag reduction on a spiked body at hypersonic speed

被引：21

作者：

d'Humieres, G. ^{[1
]}

Stollery, J. L. ^{[1
]}

机构：

[1] Cranfield Univ, Sch Engn, Bedford, England

来源：

AERONAUTICAL JOURNAL | 2010年 / 114卷 / 1152期

关键词：

FLOW;

D O I：

10.1017/S0001924000003584

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Fitting a spike on a blunt body provides a drag reduction at supersonic and hypersonic speeds. In this study, the laminar flow over a spiked.. conical body terminated by a spherical cap, inspired by the Apollo re-entry capsule design, was investigated using a hypersonic wind tunnel. Schlieren pictures revealed the absence of flow unsteadiness for the range of spike lengths tested, and force measurements showed a maximum reduction of 77% of the unspiked body drag. A simple theoretical model based on the pressure drag generated by a solid cone showed good agreement with the experimental data. The measured shock stand-off distance agreed well with predictions.

引用

页码：113 / 119

页数：7

共 15 条

[1]

Ames Research Staff, 1953, TR1135 NACA AM RES S

[2]

Crawford D. H., 1959, TN D-118

[3] Dynamics of Shock Dispersion and Interactions in Supersonic Freestreams with Counterflowing Jets [J].

Daso, Endwell O. ;

Pritchett, Victor E. ;

Wang, Ten-See ;

Ota, Dale K. ;

Blankson, Isaiah M. ;

Auslender, Aaron H. .

AIAA JOURNAL, 2009, 47 (06) :1313-1326

[4]

DHUMIERES GG, 2009, THESIS CRANFIELD U U

[5]

GILINSKY M, 2001, AIAA ASME SAE AEE 37

[6]

HILLJE ER, 1967, NASATND4185

[7]

HOLDEN MS, 1963, THESIS IMPERIAL COLL

[8]

HUTT CR, 1989, AERONAUTICAL J ROYAL, V93, P229

[9]

HUWALDT JA, 2008, SUPERSONIC CONE

[10] Experimental investigation on spiked body in hypersonic flow [J].

Kalimuthu, R. ;

Mehta, R. C. ;

Rathakrishnan, E. .

AERONAUTICAL JOURNAL, 2008, 112 (1136) :593-598

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