Hypersonic Aerothermoelastic Response Prediction of Skin Panels Using Computational Fluid Dynamic Surrogates
نویسندگان
چکیده
Computational Fluid Dynamic (CFD) surrogates are developed to efficiently compute the aerodynamic heating and unsteady pressure loads for a structurally and thermally compliant skin panel in hypersonic flow. In order to minimize the computational overhead, the surrogates are constructed using steady-state CFD flow analysis. Unsteady terms in the aerodynamic pressure are incorporated using piston theory. The surrogates are compared to both analytical modeling (i.e., piston theory and Eckerts methods) and Reynolds Averaged Navier-Stokes CFD predictions of the aerothermodynamic loads for representative panel responses. Results indicate that the surrogates accurately and efficiently reproduce CFD predictions for the aerothermodynamic loads. Comparisons of the dynamic aerothermoelastic panel response using the surrogates with previous results using analytical approaches reveal differences of over 100% in the onset time to flutter, and significantly altered post-flutter responses. The CFD surrogates are found to enable a reasonably accurate, robust, and efficient method for incorporating CFD loads prediction, which would otherwise be impractical, into a long time-record aerothermoelastic analysis of structures for a complete hypersonic trajectory.
منابع مشابه
Aeroelastic and Aerothermoelastic Analysis of Hypersonic Vehicles: Current Status and Future Trends
A review of the state-of-the-art in hypersonic aeroelasticity and aerothermoelasticity is provided. Recently, the main focus in this area has been on the development of computational aeroelastic and aerothermoelastic methods capable of studying complete hypersonic vehicles. Thus, in addition to a survey of studies conducted in this area over the past six decades, two important issues are a focu...
متن کاملUncertainty Quantification and Global Sensitivity Analysis for Hypersonic Aerothermoelastic Analysis
A novel parameterized model for temperature distribution is proposed. A framework for uncertainty quantification and global sensitivity in hypersonic aerothermoelastic analysis is developed based on this model. The uncertainty quantification and global sensitivity analysis in hypersonic aerothermoelastic analysis for control surface due to hypersonic aerothermodynamics is investigated in this s...
متن کاملFlow Variables Prediction Using Experimental, Computational Fluid Dynamic and Artificial Neural Network Models in a Sharp Bend
Bend existence induces changes in the flow pattern, velocity profiles and water surface. In the present study, based on experimental data, first three-dimensional computational fluid dynamic (CFD) model is simulated by using Fluent two-phase (water + air) as the free surface and the volume of fluid method, to predict the two significant variables (velocity and channel bed pressure) in 90º sharp...
متن کاملA Four-Field Computational Framework for the Aerothermomechanical Analysis of Hypersonic Vehicles
Hypersonic systems for space access and with strike capability are currently being researched by the Air Force. Flight testing and clearing them is particularly challenging, because of the speeds at which they operate. When anything unexpected occurs, the time to react is so short that the tested system must be destroyed. Therefore, the predictive analysis of these systems is essential for dete...
متن کاملHypersonic Aerothermoelasticity with Application to Reusable Launch Vehicles
The hypersonic aeroelastic and aerothermoelastic problem of a double-wedge airfoil typical cross-section is studied using three different unsteady aerodynamic loads: (1) third-order piston theory, (2) Euler aerodynamics, and (3) Navier-Stokes aerodynamics. Computational aeroelastic response results are used to obtain frequency and damping characteristics, and compared with those from piston the...
متن کامل