Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

The testing of aeroelastically and aerothermoelastically scaled wind-tunnel models in hypersonic flow is not feasible; thus, computational aeroelasticity and aerothermoelasticity are essential to the development of hypersonic vehicles. Several fundamental issues in this area are examined by performi...

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Bibliographic Details
Published in:AIAA journal 2008-10, Vol.46 (10), p.2591-2610
Main Authors: McNamara, Jack J, Friedmann, Peretz P, Powell, Kenneth G, Thuruthimattam, Biju J, Bartels, Robert E
Format: Article
Language:English
Subjects:
Aerodynamics
Aerospace engineering
Air flow
Analytical and numerical techniques
Compressible flows
shock and detonation phenomena
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
General theory
Heat transfer
Heating
Physics
Solid mechanics
Structural and continuum mechanics
Supersonic and hypersonic flows
Temperature effects
Vibration, mechanical wave, dynamic stability (aeroelasticity, vibration control...)
Wind tunnels
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Summary:The testing of aeroelastically and aerothermoelastically scaled wind-tunnel models in hypersonic flow is not feasible; thus, computational aeroelasticity and aerothermoelasticity are essential to the development of hypersonic vehicles. Several fundamental issues in this area are examined by performing a systematic computational study of the hypersonic aeroelastic and aerothermoelastic behavior of a three-dimensional configuration. Specifically, the flutter boundary of a low-aspect-ratio wing, representative of a fin or control surface on a hypersonic vehicle, is studied over a range of altitudes using third-order piston theory and Euler and Navier-Stokes aerodynamics. The sensitivity of the computational-fluid-dynamics-based aeroelastic analysis to grid resolution and parameters governing temporal accuracy are considered. In general, good agreement at moderate-to-high altitudes was observed for the three aerodynamic models. However, the wing flutters at unrealistic Machnumbers in the absence of aerodynamic heating. Therefore, because aerodynamic heating is an inherent feature of hypersonic flight and the aeroelastic behavior of a vehicle is sensitive to structural variations caused by heating, an aerothermoelastic methodology is developed that incorporates the heat transfer between the fluid and structure based on computational-fluid-dynamics-generated aerodynamic heating. The aerothermoelastic solution procedure is then applied to the low-aspect-ratio wing operating on a representative hypersonic trajectory. In the latter study, the sensitivity of the flutter margin to perturbations in trajectory angle of attack and Mach number is considered. Significant reductions in the flutter boundary of the heated wing are observed. The wing is also found to be susceptible to thermal buckling. [PUBLICATION ABSTRACT]
ISSN:0001-1452
1533-385X
DOI:10.2514/1.36711