FURTHER INVESTIGATIONS OF TRANSONIC SHOCK-WAVE BOUNDARY-LAYER INTERACTION WITH PASSIVE CONTROL

被引：10

作者：

RAGHUNATHAN, S

MCILWAIN, ST

机构：

[1] Queen’s University, Belfast

来源：

JOURNAL OF AIRCRAFT | 1990年 / 27卷 / 01期

关键词：

D O I：

10.2514/3.45896

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Passive control experiments were conducted on a wall-mounted half-model, with a supercritical profile, in a small transonic tunnel. The shock Mach number Mso was in the range 1.2 < Mso < 1.34. The momentum thickness Reynolds number Re at the foot of the shock was 5.7 × 103. The results indicated that a significant drag reduction in transonic flow can be obtained by passive control, which was broadly in agreement with similar experiments conducted at Rensselaer Polytechnic Institute at Rθ = 3 × 103 and experiments conducted at Queen’s University, Belfast, on a circular arc model at Rθ = 10 × 104. © 1989 by S. Raghunathan and S. T. Mcllwain. © The American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

引用

页码：60 / 65

页数：6

共 10 条

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[2]

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[7]

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[8]

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[10]

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