P. R. Viswanath
National Aerospace Laboratories
22 Papers
144 Citations
P. R. Viswanath is an academic researcher from National Aerospace Laboratories. The author has contributed to research in topics: Drag & Boundary layer. The author has an hindex of 11, co-authored 22 publications.
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Papers
Relaminarization in highly favourable pressure gradients on a convex surface
TL;DR: In this paper, a coupled piezoelectric finite element formulation involving a hygrothermal strain field is derived using the virtual work principle and is employed in a nine-noded field consistent Lagrangian element.
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Nose Bluntness for Side-Force Control on Circular Cones at High Incidence
TL;DR: In this paper, the effect of nose bluntness on the characteristics of vortex asymmetry and induced side forces on slender cone models at low speeds was investigated, and the results showed that the onset of vortex-asymmetry with nose blunting correlates with geometrical parameters and is practically independent of Reynolds number.
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Separation control by tangential blowing inside the bubble
TL;DR: In this paper, the authors investigated the effectiveness of steady tangential blowing inside the separation bubble to control axisymmetric separated flow at low speeds and showed that blowing downstream of the separation location, but within the bubble, can be an effective means of separation control considering both wall and wake flow reversals.
Base Drag Reduction Caused by Riblets on a GAW(2) Airfoil
Channa Raju,P. R. Viswanath +1 more
TL;DR: In this paper, the effect of 3M riblet sheers on the base pressure of an airfoil with a blunt trailing edge was investigated. And the results showed very clearly that the base drag reduction of an engineering value can be achieved for the optimized 3M Riblet geometry.
Drag Reduction from Square-Base Afterbodies at High Speeds
N. B. Mathur,P. R. Viswanath +1 more
TL;DR: In this article, a family of axisymmetric afterbodies with conical and circular arc boat tails having the same annular base area and jet flow parameters were evaluated in the 0.5m base flow wind tunnel at high speeds.
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