Influence of Small Attack Angles on the Transition on the Wing with the Subsonic Leading Edge at M=2

被引：0

作者：

Semionov, N., V ^{[1
]}

Kosinov, A. D. ^{[1
,2
]}

Yermolaev, Yu G. ^{[1
,2
]}

Kocharin, V. L. ^{[1
]}

Shipul, S. A. ^{[1
,2
]}

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

机构：

[1] Khristianovich Inst Theoret & Appl Mech SB RAS, Inst Skaya Str 4-1, Novosibirsk 630090, Russia

[2] Novosibirsk State Univ, Pirogova 2, Novosibirsk 630090, Russia

来源：

HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2020) | 2020年 / 2288卷

基金：

俄罗斯基础研究基金会;

关键词：

BOUNDARY-LAYER; NUMBER;

D O I：

10.1063/5.0028295

中图分类号：

O59 [应用物理学];

学科分类号：

摘要：

The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72 at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.

引用

页数：5

共 50 条

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[2] SUBSONIC WING-BODY INTERFERENCE FOR MISSILE CONFIGURATIONS AT LARGE ANGLES OF ATTACK
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