Library Subscription: Guest
Begell Digital Portal Begell Digital Library eBooks Journals References & Proceedings Research Collections
TsAGI Science Journal

ISSN Print: 1948-2590
ISSN Online: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.v42.i1.10
pages 1-12

EXPERIMENTAL INVESTIGATION OF THE SUPERSONIC BOUNDARY LAYER STABILITY ON A SWEPT WING AT MACH NUMBER M = 2

Yu. G. Ermolaev
Khristianovich Institute of Theoretical and Applied Mechanics, Institutskaya str. 4/1, Novosibirsk, 630090, Russia
A. D. Kosinov
Khristianovich Institute of Theoretical and Applied Mechanics, Institutskaya str. 4/1, Novosibirsk, 630090, Russia
N. V. Semionov
Khristianovich Institute of Theoretical and Applied Mechanics, Institutskaya str. 4/1, Novosibirsk, 630090, Russia

ABSTRACT

The experimental data of the investigation of stability of a 3D supersonic boundary layer on a swept wing are presented. The experiments are performed on a swept-wing model with a lenticular airfoil, with a swept angle of the leading edge of 45 deg, and at Mach number M = 2. Development of natural disturbances on the model of a thin swept wing is studied in detail on the basis of measurements. The characteristic regions of disturbance development are obtained. The Reynolds number of the region of instability of secondary flow disturbances is experimentally determined. It is shown that the secondary instability of a cross flow plays the main role in a laminar flow transition in the supersonic boundary layer on the swept-wing model.