Accession Number:

ADA394907

Title:

Navier-Stokes Computations of Finned Missiles at Supersonic Speeds

Descriptive Note:

Rept. for Jul 1997-Jul 2000

Corporate Author:

ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD

Report Date:

2001-09-01

Pagination or Media Count:

15.0

Abstract:

The U.S. Army Research Laboratory ARL is interested in applying state-of-the-art high performance computing tools to predict the aerodynamics of Army shell at angle of attack for a wide range of Mach number from high subsonic to high supersonic. In this paper, the WIND flow solver has been used to study the aerodynamics of two missile configurations. The GridPro grid generation software has been utilized to generate the computational grids. Several aspects of interest concerning the generation of grids for use with WIND and the process of obtaining solutions is discussed. Comparisons are shown between computation and experiment for several turbulence models.

Subject Categories:

  • Aerodynamics
  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE