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Recent Enhancements to USM3D Unstructured Flow Solver for Unsteady FlowsThe NASA USM3D unstructured flow solver is undergoing extensions to address dynamic flow problems in support of NASA and NAVAIR efforts to study the applicability of Computational Fluid Dynamics tools for the prediction of aircraft stability and control characteristics. The initial extensions reported herein include two second-order time stepping schemes, Detached-Eddy Simulation, and grid motion. This paper reports the initial code verification and validation assessment of the dynamic flow capabilities of USM3D. The cases considered are the classic inviscid shock-tube problem, low Reynolds number wake shedding from a NACA 0012 airfoil, high Reynolds number DES-based wake shedding from a 4-to-1 length-to-diameter cylinder, and forced pitch oscillation of a NACA 0012 airfoil with inviscid and turbulent flow.
Document ID
20040105603
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Pandya, Mohagna J. (Swales Aerospace Hampton, VA, United States)
Frink, Neal T. (NASA Langley Research Center Hampton, VA, United States)
Abdol-Hamid, Khaled S. (NASA Langley Research Center Hampton, VA, United States)
Chung, James J. (Naval Air Systems Command Patuxent River, MD, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2004
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2004-5201
Meeting Information
Meeting: 22nd AIAA Applied Aerodynamics Conference and Exhibit
Location: Providence, RI
Country: United States
Start Date: August 16, 2004
End Date: August 19, 2004
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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