Control of incident shock-induced separation using vane-type vortex-generating devices.

Verma, S.B. and Manisankar, C. (2018) Control of incident shock-induced separation using vane-type vortex-generating devices. AIAA Journal, 56 (4). pp. 1600-1615. ISSN 00011452

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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 5δ 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=5δ 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.

Item Type: Article
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aerodynamics
Depositing User: Mrs SK Pratibha
Date Deposited: 25 Feb 2020 14:26
Last Modified: 25 Feb 2020 14:26

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