Coupled Vertical/Short Takeoff and Landing (VSTOL) Down Wash-Ground Effect and Ship Air Wake Turbulent Flow Simulation Model

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-03-C-0114
Agency Tracking Number: N012-0270
Amount: $749,924.00
Phase: Phase II
Program: SBIR
Awards Year: 2003
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
6210 Keller's Church Road, Pipersville, PA, 18947
DUNS: 929950012
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Neeraj Sinha
 Vice President & Technica
 (215) 766-1520
Business Contact
 Neeraj Sinha
Title: Vice President & Technica
Phone: (215) 766-1520
Research Institution
The proposed effort entails the development of a CFD simulation framework for the modeling of coupled airwake-V/STOL flow fields. A novel strategy that combines a compressible and an incompressible flow solver is proposed, in which, the different regionsof the flow are computed using algorithms that are optimal for the respective regimes. Each flow solver will be validated in detail for the simulation of the respective regimes by comparisons with measurements at laboratory scale as well as full scale. Anunsteady turbulence model for the simulation of V/STOL flow fields is also proposed in which modern enhancements to Reynolds Averaged Navier Stokes (RANS) turbulence modeling will be incorporated into the solvers. Large Eddy Simulations (LES) of laboratoryscale flow fields will be used to develop and calibrate the unsteady model for the flow fields of interest. Finally, development of a strategy to interface the two solvers using a novel dynamical modeling technique that will reduce the computationalexpense is also proposed. Upon completion, this simulation framework will aid in the development of flight simulator models used in the integration of new aircraft units with air capable naval platforms. The simulation framework is based on CRAFT Tech'sunstructured CRUNCH CFD code. The proposed Phase II program will lead to the development and demonstration of a Dynamic Interface (DI) Toolkit, with a coupled Compressible-Incompressible modeling methodology for simulating high-speed V/STOL exhaustsembedded in low-speed airwakes. This toolkit is of critical value in the integration of the JSF into the Naval fleet. The DI Toolkit is of a fundamental nature and has broad-based applicability to a range of emerging applications, e.g. active controllerdevelopment, shear flow control, noise attenuation, high angle-of-attack aerodynamic modeling etc.

* information listed above is at the time of submission.

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