Analytical investigation of supersonic panel flutter under thermal environment with arbitrary flow direction

Mukherjee, Somenath and Deepa, N and Avinash, R and Manjuprasad, M and Viswanath, S (2007) Analytical investigation of supersonic panel flutter under thermal environment with arbitrary flow direction. Technical Report. National Aerospace Laboratories, Bangalore, India.

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    Abstract

    Panels and Thermal Protection System of re-entry vehicles are subjected to a wide range of flow condition during ascent and reentry phases. The flow can vary from subsonic continuum flow to hypersonic rarefied flow with wide ranging dynamic pressure and associated aerodynamic heating. One of the main design considerations is the assurance of panel safety against panel flutter under the flow conditions characterized by harsh thermal environment. The objectives of this work are to understand the physical principles behind panel flutter under supersonic flow with arbitrary flow angles and given thermal profiles, to make an estimate of the lowering of the critical dynamic pressure (flutter boundary) of the panels due to high thermal distributions in the restrained panels. Using analytical techniques, a mathematical formulation has been developed which can predict flutter boundaries under parabolic distribution of temperature, in addition to the flat temperature profile, over the panels.13; The piston theory is used for aerodynamic pressure computations. Studies have been carried out for rectangular panels of various aspect ratios subjected to flat and parabolic type thermal profiles and various flow directions (restricted on the plane of the panels). The theoretical results are validated with the finite element software package NASTRAN for no thermal condition and flow along x-direction. It has been observed that the flutter boundaries fall sharply with temperature, indicating that a careful study of the actual panels of the vehicle under the anticipated thermal profiles is necessary for design purpose. Furthermore, it has been observed that for any rectangular panel, flow along the longer side is most critical.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Supersonic panel flutter;Critical dynamic pressure;Flutter speed;Thermal profile;Aspect ratio;Flow direction;In-plane loads
    Subjects: ENGINEERING > Structural Mechanics
    Division/Department: Structures Division, Other, Other, Other, Structures Division
    Depositing User: M/S ICAST NAL
    Date Deposited: 16 Jan 2009
    Last Modified: 17 Jun 2010 10:34
    URI: http://nal-ir.nal.res.in/id/eprint/4649

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