An experimental investigation was conducted to control an incident shock-induced boundary-layer separation associated with a 14 deg shock generator in a Mach 2.05 flow. Two vane-type configurations, namely the triangular ( h / δ = 0.3 , 0.5, 0.8, 1.0) and the rectangular ( h / δ = 0.5 ) designs, were studied. An array of each control device was tested for three control locations of X / δ = 5 , 10, and 15. The control location of 5 δ is seen to show the maximum reduction in separation length for each device tested. For the rectangular-vane device ( h / δ = 0.5 ), a maximum reduction of 38% in separation length is observed, followed by the triangular-vane devices of h / δ = 0.8 and 1.0, each of which shows a 32% reduction, and finally, h / δ = 0.5 with 18%. The effectiveness of these devices to control separation is, however, seen to decrease with increase in X / δ . In terms of separation shock unsteadiness, the maximum rms value for X / δ = 5 δ shows the highest value for each control device, and this value decreases with increase in control location. At X / δ = 15 , both the rectangular vane ( h / δ = 0.5 ) and triangular vane ( h / δ = 0.8 , 1.0 ) show a 50% reduction in maximum rms value, whereas it decreases to 30% at X / δ = 10 for these devices.


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    Title :

    Control of Incident Shock-Induced Separation Using Vane-Type Vortex-Generating Devices


    Contributors:

    Published in:

    AIAA Journal ; 56 , 4 ; 1600-1615


    Publication date :

    2018-01-23


    Size :

    16 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






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