Experimental study of compressible boundary layer on a cone at angles of attack

被引：10

作者：

Maslov, A. ^{[1
,2
]}

Bountin, D. ^{[1
,2
]}

Shiplyuk, A. ^{[1
,2
]}

Sidorenko, A. ^{[1
,2
]}

Shen, Q. ^{[3
]}

Bi, Z. ^{[3
]}

机构：

[1] Khristianovich Inst Theoret & Appl Mech ITAM, Novosibirsk 630090, Russia

[2] Novosibirsk State Univ, Novosibirsk 630090, Russia

[3] CAAA, Beijing 100074, Peoples R China

来源：

ACTA MECHANICA SINICA | 2009年 / 25卷 / 03期

基金：

俄罗斯基础研究基金会;

关键词：

Compressible boundary layer; Transition; Experimental study; TRANSITION; STABILITY;

D O I：

10.1007/s10409-009-0228-8

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

Experimental study was conducted for boundary-layers on a sharp 5A degrees half-angle cone of 400 mm length at angles of attack. The model was tested in the T-326 hypersonic wind tunnel (ITAM) at freestream Mach number M = 5.95. Mean and fluctuation wall characteristics of the boundary layer are measured at 0A degrees, 2A degrees, 3A degrees and 4A degrees angles of attack for different stagnation pressures. Pulsation measurements are carried out by means of ALTP sensor. Pressure and temperature distributions along the model are obtained, and transition beginning and end locations have been found. Boundary layer stabilization with the increase of angle of attack and the decrease of stagnation pressure is observed. High frequency pulsations inherent to hypersonic boundary layer (second mode) have been detected.

引用

页码：325 / 333

页数：9

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