Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow
Jack J. McNamara,Jack J. McNamara,Peretz P. Friedmann,Kenneth G. Powell,B. J. Thuruthimattam,Robert E. Bartels +5 more
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In this article, the authors performed a systematic computational study of the hypersonic aeroelastic and aerothermoelastic behavior of a three-dimensional configuration of a low-aspect-ratio wing.Abstract:
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 Mach numbers 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.read more
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Investigation of the Heat Transfer Coefficients on the Body Surface in High Speed Flow
Yuri Ivanovich Khlopkov,Vladimir Alekseevich Zharov,Zay Yar Myo Myint,Anton Yurievich Khlopkov +3 more
TL;DR: In this paper, the authors present the methods for calculating the heat transfer coefficients on surface of high-speed aircrafts in laminar and turbulent boundary layer at high speed flows.
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Numerical investigation of aerothermoelastic characteristics of a thin heated panel in high supersonic and hypersonic flow
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The analysis on the flow characteristics of supersonic inlet considering structural vibration
TL;DR: In this paper , the influence of the structural vibration of the compression surface on the inlet's performance is evaluated. And the influence is more obvious when the vibration occurs to be more closed to the lip.
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Simulation of flow and heat transfer characteristic in the combined thermal and acoustic environment
TL;DR: In this article, a flow and heat transfer model in the combined thermal and acoustic environment was established and the temperature distributions of the test pieces in different heat flux densities with two installation locations of the graphite heater (inside the duct and on the duct) were calculated and analyzed by the CFD method combined with DO radiation model.
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