Numerical solutions of Navier-Stokes equations for a Butler wingThe flow field is simulated on the surface of a Butler wing in a uniform stream. Results are presented for Mach number 3.5 and Reynolds number of 2,000,000. The simulation is done by integrating the viscous Navier-Stokes equations. These equations govern the unsteady, viscous, compressible and heat conducting flow of an ideal gas. The equations are written in curvilinear coordinates so that the wing surface is represented accurately. The O-type and H-type grids have been used for this study, and results are compared. The governing equations are solved by the MacCormack time-split method, and the results are compared with other theoretical and experimental results. The codes are written in FORTRAN, vectorized and currently run on the CDC Vector Processing System (VPS-32) computer.
Document ID
19870035481
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Abolhassani, Jamshid S. (Old Dominion Univ. Norfolk, VA, United States)
Tiwari, Surendra N. (Old Dominion University Norfolk, VA, United States)
Smith, Robert E. (NASA Langley Research Center Hampton, VA, United States)