Stability of high-speed boundary layer on a sharp cone with localized wall heating or cooling

V. G. Soudakov; A. V.  Fedorov; I. V. Egorov

doi:10.1051/eucass/201507569

All issues

Volume 7 (2015)

10.1051/eucass/201507569

Abstract

Open Access

Issue		Volume 7, 2015 Progress in Flight Physics – Volume 7


Page(s)		569 - 584
Section		Stability and transition
DOI		https://doi.org/10.1051/eucass/201507569
Published online		08 June 2015

Progress in Flight Physics 7 (2015) 569-584

Stability of high-speed boundary layer on a sharp cone with localized wall heating or cooling

V. G. Soudakov¹^,2, A. V. Fedorov¹^,2 and I. V. Egorov¹^,2

¹ Moscow Institute of Physics and Technology 16 Gagarina Str., Zhukovsky, Moscow Region 140180, Russia
² Central Aerohydrodynamic Institute (TsAGI) 1 Zhukovsky Str., Zhukovsky, Moscow Region 140180, Russia

Abstract

A localized heating or cooling effect on stability and transition of the boundary layer flow on a sharp cone is analyzed at the Mach number 6. The mean flows are calculated using axisymmetric Navier-Stokes equations. The spatial linear stability analysis is performed for twodimensional (2D) disturbances related to the Mack second mode. The transition onset points are estimated using the e^N method. In this framework, the heater or cooler may cause earlier or later transition depending on the choice of critical N-factor. Direct numerical simulations (DNS) of 2D wave propagating in the boundary layer are compared with stability results.