Vasily V. Vedeneev , Victor A. Nesterov , Alexander L. Medvedskii, Kirill I. Sypalo

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018-1174

In the flutter analysis of flight vehicle structures moving at moderate supersonic speeds, the air is usually considered as perfect gas, and the unsteady aerodynamic pressure can be calculated through linearised aerodynamic theory. At high supersonic and hypersonic speeds, two effects become significant. First, aerodynamic nonlinearity essentially affects limit cycle amplitudes and should be taken into account. Second, in the hypersonic flight the flow at high temperatures produced by the bow shock is a reacting mixture and cannot be considered as a perfect gas. While the aerodynamic nonlinearity effect was excessively studied in literature, the reacting flow effect with respect to flutter was not studied previously. In this paper we analyse the changes in the flutter theory produced by the effect of chemical reactions. As an example, we analyse the flutter boundary of a flat skin panel in the reacting flow.

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In Categories: Boundary Layer Control, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2018, Hypersonic Aerodynamics, Hypersonic Flight Dynamics
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