A closed-form analytical model for predicting 2D boundary layer displacement thickness for verification, calibration and validation of navier-stokes solvers

Sanal Kumar, VR and Sankar, V and Natarajan, V and Chandrasekaran, N and Vignesh, S and Sathyan, P and Sulthan Ariff Rahman, M and Roshan Vignesh, B and Ukeshkumar, H (2018) A closed-form analytical model for predicting 2D boundary layer displacement thickness for verification, calibration and validation of navier-stokes solvers. In: 48th AIAA Fluid Dynamics Conference, 2018, 25 - 29 June 2018, Atlanta, Georgia.

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Abstract

An infallible analytical methodology has been discovered for predicting the boundary layer blockage at the Sanal flow choking condition for solving the 2D diabatic fluid flow problems in physical and biological sciences. This is the continuation of the previous connected paper pertaining to the boundary layer blockage prediction for choked adiabatic flows (V. R. Sanal Kumar et al.[1], AIP Advances, 8, 025315, 2018). The Sanal flow choking for diabatic flow is a unique condition of any internal flow system at which both thermal choking and the wall-friction induced flow choking occur at a single sonic-fluid-throat location. A constant area conduit with large length-to-diameter ratio (l/d ≥ 27) followed by a divergent duct is selected as a two-dimensional physical model. The novelty of the closed-form analytical model presented herein is that without missing the flow physics we could predict the exact boundary-layer blockage at the sonic fluid-throat location from the known values of the inlet port diameter of the physical model, inlet Mach number, and the heat capacity ratio of the gas. Note that any Navier-Stokes solver calibrated using this closed-form analytical model warrants the capability for featuring the laminar-turbulent-transition in an internal flow system from the known values of the axial Mach number. Furthermore, if we know the axial Mach number of any internal flow system the exact value of the local boundary layer thickness can be predicted using this closed-form analytical model. The exact solution obtained from the proposed methodology can be taken as a credible benchmark data for the verification, calibration and validation of various viscous flow solvers as well as the flow meters, involving the transfer of heat, for various aerospace applications.

Item Type:	Conference Paper
Publication:	2018 Fluid Dynamics 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:	Aerodynamics; Aerospace applications; Analytical models; Benchmarking; Boundary layers; Calibration; Forecasting; Mach number; Navier Stokes equations; Specific heat, Analytical methodology; Boundary layer thickness; Calibration and validations; Displacement thickness; Fluid flow problems; Laminar turbulent transitions; Length to diameter ratio; Navier-Stokes solver, Boundary layer flow
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	27 Aug 2022 05:31
Last Modified:	27 Aug 2022 05:31
URI:	https://eprints.iisc.ac.in/id/eprint/76030

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