Experimental data and results of numerical simulation of a supersonic flow over a blunt cone are presented. Experimental investigations of the effect of local cooling or heating of the nose of the model on the laminar-turbulent transition on sharp and blunt cones were carried out in two hypersonic wind tunnel ITAM SB RAS - IT-302M and “Transit-M.” Numerical simulation were performed using the commercial package ANSYS Fluent and transition modelγ- Reθt. The computed results of the heat flux on the cone surface are compared with the data of wind tunnel experiments performed at the flow Mach number М∞ = 5.8 and 5.95. It is shown an ambiguous effect of local impact for different conditions of the flow.
Effect of local heating/cooling on the laminar-turbulent transition on a blunted cone
INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2016): Proceedings of the 18th International Conference on the Methods of Aerophysical Research ; 2016 ; Perm, Russia
AIP Conference Proceedings ; 1770 , 1
2016-10-13
6 pages
Conference paper
Electronic Resource
English
Effect of roughness of the blunted cone nose-tip on laminar-turbulent transition
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