Aerodynamics and Flow-Physics Laboratory

Dr. Rinku Mukherjee

Department of Applied Mechanics

IIT Madras, Chennai, India 600036



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Sponsored Research

Completed

  1. MWAT: Morphing Wing Aircraft Technologies

    One of three verticals of Centre For Propulsion Technologies

    Funding Agency: DRDO (Defence Research and Development Organisation, India)

    Value: ~1 Crore INR (Individual Share among 4 projects)

    Time: 2017-2022

    Aim of the project: Build a prototype of a rectangular wing which can change its camber along span during flight.

    Achievements: Experimental Studies conducted for validation of "Decambering Technique". Boundary Layer Control Technique using the same tested vigorously using both experiments and numerical analysis. Both Steady-state and Unsteady numerical analysis and wind tunnel experiments conducted. Change in camber using MFC actuated external skin demonstrated.

    Conclusion:"Decambering Technique" is a useful tool for boundary layer control.

    Likely Application of the Outcome:

    1 PhD (Dr. Aritras Roy) graduated.

    2 Copyrights for numerical codes and 1 patent has been filed.

    Hopefully some aerospace agency takes notice !!



  2. A Numerical Study of the Unsteady Wake Vortices of a Pitching Wing

    Funding Agency: ARDB (Aeronautics Research and Development Board) of DRDO (Defence Research and Development Organisation, India)

    Value: 17.5 Lakhs INR (Individual Project Investigator(PI))

    Time: 2015-2017

    Aim of the project: Numerical Analysis and Experimental Validation of Unsteady Aerodynamics of a pitching wing.

    Achievements: Numerical Code Developed for Unsteady pre and post-stall aerodynamics, Experimental facility set-up and priliminary pressure readings and load readings undetaken for a fixed wing.

    Conclusion:A multi-dimensional post-stall predictive tool is developed for wing(s) using VLM, which uses a nascent vortex to account for flow separation. The tool is robust for wings with cambered airfoil sections but some convergence issues exist for wings with symmetric airfoil sections. In case of non-convergence, the blow-up seems to usually occur near the tips and before the blow up there is marked asymmetry along span. For wings with cambered airfoil sections, section Cl distributions are completely devoid of sawtooth. Different initial conditions do not result in multiple solutions.

    Likely Application of the Outcome: Technology for high-left devices. For example, aircrafts, which can climb or dip very sharply at very high angles of attack.



  3. Prediction of 2D and 3D aerodynamic characteristics for unsteady post-stall flow

    Funding Agency: ARDB (Aeronautics Research and Development Board) of DRDO (Defence Research and Development Organisation, India)

    Value: 8.178 Lakhs INR (Individual Project Investigator(PI))

    Time: 2010-2012

    Aim of the project: Numerical Analysis and Experimental Validation of Unsteady Aerodynamics of a pitching wing.



  4. A study of unsteady pre and post-stall flow regimes past multiple-lifting surfaces

    Funding Agency: IITM (Indian Institute of Technology Madras) NFSG (New Faculty Seed Grant)

    Value: 5.0 Lakhs INR (Individual Project Investigator(PI))

    Time: 2008-2011

    Aim of the project: Post-Stall aerodynamics of unsteady flow past multiple lifting surfaces.