Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

V. Borovoy; V. Mosharov; A. Noev; V. Radchenko

doi:10.1051/eucass/201203015

All issues

Volume 3 (2012)

10.1051/eucass/201203015

Abstract

Open Access

Issue		Volume 3, 2012 Progress in Flight Physics


Page(s)		15 - 24
Section		Chapter One. Aerodynamics
DOI		https://doi.org/10.1051/eucass/201203015
Published online		29 January 2013

Progress in Flight Physics 3 (2012) 15-24

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

V. Borovoy, V. Mosharov, A. Noev and V. Radchenko

Central Aerohydrodynamic Institute (TsAGI) Zhukovsky, Str. 1 Zhukovsky, Moscow region 140180, Russia

Abstract

Application of Temperature Senstive Paint (TSP) technology for investigation of boundary layer transition in short-duration wind tunnels is presented. Investigations were made on sharp and blunted flat plates in UT-1 wind tunnel of TsAGI operated in Ludwieg scheme at Mach numbers 5, 6, and 8 (Reynolds numbers from 5.5 · 10⁶ to 26 · 10⁶). Both natural and induced boundary layer transitions were investigated.