Affiliation:
1. Khristianovich Institute of Theoretical and Applied Mechanics, Novosibirsk, Russia
Abstract
The effect of plasma actuators on shock wave–laminar boundary layer interaction was studied experimentally on transonic laminar aerofoil. The unsteady characteristics of the separation zone including the transonic buffet were measured. Two kinds of electrical discharge actuators were used for the flow control. Successful suppression of separated flow and laminar transonic buffet by plasma actuators was demonstrated. An analysis of the effect of power and frequency of the discharge on shock wave–laminar boundary layer interaction was carried out. High efficiency ratio of the separation control by plasma actuators was achieved in the experiments.
Funder
Russian Foundation for Basic Research
Supported by Airbus under Research and Technology Contract
Subject
Mechanical Engineering,Aerospace Engineering
Cited by
11 articles.
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