Studies on 2D and 3D boundary layer blockage and external flow choking at moving wing in ground effect

Sanal Kumar, VR and Saravanan, V and Srinivasan, V and Ganesh Shankar, S and Mani, S and Sankar, V and Rahman M, SA and Natarajan, D and Krishnamoorthy, D (2018) Studies on 2D and 3D boundary layer blockage and external flow choking at moving wing in ground effect. In: 36th AIAA Applied Aerodynamics Conference, 2018, 25 - 29 June 2018, Atlanta, Georgia.

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Abstract

The boundary-layer blockage induced flow choking is a seminal research topic of topical interest. Herein, using a validated 2D Delayed Detached Eddy Simulation model (DDES), attempts have been made to examine the influence of boundary-layer blockage on external flow choking at fixed and moving wing-in-ground (WIG) effect. As a part of the DDES code validation and calibration, the numerically predicted boundary-layer blockage at the Sanal flow choking condition for adiabatic channel flows is verified using the closed-form analytical model of Sanal Kumar V. R. et al. (AIP Advances, 8, 025315, 2018) 1 and found excellent agreement with the exact solution. Through the comprehensive 2D numerical studies, we inferred that at the identical WIG effect conditions the stationary airfoil exhibits an early external flow choking than the moving airfoil due to the higher value (~393 %) of boundary-layer-blockage. We discerned the boundary-layer blockage induced sonic location at 55 % of the chord-length for fixed-wing-in-ground-effect (FWIG) and 70 % for moving-wing-in-ground (MWIG) effect craft from the leading-edge. During the 3D simulation of FWIG craft cases we observed that facilitating a variable depth channel with stagnation flow effect at the bottom surface of the fuselage increases the overall lift coefficient and reduces the possibilities of the external flow choking at WIG effect. We concluded that, in lieu of the FWIG effect case studies, it is invariably beneficial to go for a realistic simulation of the MWIG effect, which is analogous and would have the aspects of a real-time parametric flow.

Item Type:	Conference Paper
Publication:	2018 Applied Aerodynamics Conference
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	The copyright for this article belongs to the American Institute of Aeronautics and Astronautics Inc, AIAA.
Keywords:	Airfoils; Boundary layers; Fixed wings; Ground effect, Bottom surfaces; Code validation; Delayed-detached eddy simulation; Lift coefficient; Realistic simulation; Research topics; Stagnation flows; Wing in ground effect, Boundary layer flow
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	20 Aug 2022 06:00
Last Modified:	20 Aug 2022 06:00
URI:	https://eprints.iisc.ac.in/id/eprint/76022

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