Towards Better Modeling and Simulation of Nonlinear Aeroelasticity On and Beyond Transonic Regimes

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,577.00
Award Year:
2011
Program:
SBIR
Phase:
Phase I
Contract:
NNX11CG73P
Award Id:
n/a
Agency Tracking Number:
104727
Solicitation Year:
2010
Solicitation Topic Code:
A2.04
Solicitation Number:
n/a
Small Business Information
KY, Lexington, KY, 40511-1628
Hubzone Owned:
N
Minority Owned:
Y
Woman Owned:
N
Duns:
790637867
Principal Investigator:
Patrick Hu
Principal Investigator
(859) 699-0441
patrick.g.hu@advanceddynamics-usa.com
Business Contact:
Patrick Hu
Business Official
(859) 699-0441
patrick.g.hu@advanceddynamics-usa.com
Research Institution:
Stub




Abstract
The need to accurately predict aeroelastic phenomenon for a wide range of Mach numbers is a critical step in the design process of any aerospace vehicle. Complex aerodynamic phenomenon such as vortex shedding, shock-turbulence interaction, separation, etc. dominate at transonic and supersonic Mach numbers and hence the need to address these phenomena is of utmost importance in the modeling process. Research is proposed for the development and implementation of state of the art, large-eddy-simulation (LES) based computational models for problems in nonlinear aeroelasticity. Highly efficient and accurate subgrid-scale (SGS) models will be incorporated into the flow solver and coupled with high fidelity structure solvers to predict aeroelastic phenomena such as transonic flutter, limit cycle oscillations, etc. The SGS models proposed are based on eddy-viscosity and non-eddy-viscosity models and they will both be assessed for accuracy and robustness in the context of nonlinear aeroelasticity. The implications of the proposed work include using highly accurate turbulence models with efficient finite element models of structure to solve problems in nonlinear aeroelasticity. The application of the proposed innovations spans the range of flight, from subsonic to supersonic transport vehicles. Anticipated results include 1) the implementation of the proposed LES methodology into current aeroelastic toolset 2) application of the proposed work to large-scale simulation and comparison with experiment and lower fidelity RANS-based aeroelastic simulations and 3) advancement of the state of knowledge for nonlinear problems in aeroelasticity.

* information listed above is at the time of submission.

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