A Novel CFD Method to Estimate Heat Transfer Coefficient for High Speed Flows

  • A. Bhandarkar Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad
  • Malsur Dharavath Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad
  • M.S.R. Chandra Murty Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad
  • P. Manna Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad
  • Debasis Chakraborty Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad
Keywords: Aerodynamic heating, heat flux, thermal analysis, computational fluid dynamics, scramjet combustor

Abstract

Accurate prediction of surface temperature of high speed aerospace vehicle is very necessary for the selection of material and determination of wall thickness. For aerothermal characterisation of any high speed vehicle in its full trajectory, it requires number of detailed computational fluid dynamics (CFD) calculations with different isothermal calculations. From the detailed CFD calculations for different flow conditions and geometries, it is observed that heat transfer coefficients scale with the difference of adiabatic wall temperature and skin temperature. A simple ‘isothermal method’, is proposed to calculate heat flux data with only two CFD simulations one on adiabatic condition and other on isothermal condition. The proposed methodology is validated for number of high speed test cases involving external aerodynamic heating as well as high speed combusting flow. The computed heat fluxes and surface temperatures matches well with experimental and flight measured values.

Author Biographies

A. Bhandarkar, Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad

Mr A. Bhandarkar obtained his MTech in Mechanical Engineering from IIT, BHU. Presently he is working as a Scientist at the Defence Research and Development Laboratory (DRDL), Hyderabad. His research areas include : Aerodynamic heating, droplet break-up study for high-speed flow, two phase flow analysis, CHT analysis, etc.

Malsur Dharavath, Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad

Mr Malsur Dharavath obtained his ME (Aerospace Engineering) from Indian Institute of Science (IISc), Bengaluru and is working as a Scientist at the Defence Research and Development Laboratory (DRDL), Hyderabad. His research areas include Highspeed reacting and non-reacting flows in missile propulsion, scramjet propulsion, free-and confined -supersonic jets etc.

M.S.R. Chandra Murty, Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad

Mr M.S.R. Chandra Murty obtained his BTech (Mech Engg) from Regional Engineering College (REC), Warangal. He is currently working as Scientist in Computational Combustion Dynamics Division, Defence Research and Development Laboratory (DRDL), Hyderabad. His research interest includes heat transfer and computational fluid dynamics related to aerospace propulsion.

P. Manna, Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad

Dr P. Manna obtained his PhD (Thermal Science and Engineering) from IIT, Kharagpur. Presently he is working as a Scientist in the Directorate of Computational Dynamics, DRDL, Hyderabad. His research interests include: CFD, propulsion, heat transfer, and high-speed reacting flow.

Debasis Chakraborty, Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad

Dr Debasis Chakraborty obtained his PhD in Aerospace Engineering from Indian Institute of Science, Bengaluru. Presently, working as Technology Director, Computational Dynamics Directorate, DRDL, Hyderabad. His research interests are : CFD, aerodynamics, high-speed combustion, and propulsion.

Published
2016-04-25
How to Cite
BhandarkarA., DharavathM., Chandra MurtyM., MannaP., & ChakrabortyD. (2016). A Novel CFD Method to Estimate Heat Transfer Coefficient for High Speed Flows. Defence Science Journal, 66(3), 203-209. https://doi.org/10.14429/dsj.66.8873
Section
Aeronautical Systems

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