Accession Number:

ADA503640

Title:

Missile Base Flow: Hybrid RANS/LES Computational Fluid Dynamics Comparisons to Measurements

Descriptive Note:

Conference paper

Corporate Author:

ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING CENTER REDSTONE ARSENAL AL

Report Date:

2008-12-01

Pagination or Media Count:

8.0

Abstract:

Combined Computational Fluid Dynamics Reynolds Averaged Navier-Stokes and LES model calculations were completed for comparisons with wind tunnel measurements of flow along the afterbody and in the base region of a circular cylinder aligned to a Mach 2.5 freestream. This cylinder is representative of a missile at zero degrees angle-of-attack. Comparison data includes afterbody and base pressure, high quality non-intrusive Laser Doppler Velocimetry and Pressure Sensitive Paint measurements, and turbulent kinetic energy. The flow in the baseseparated region of a tactical missile is very complex even though the geometry is quite simple. There are several reasons this is the case. First, the external flow over the missile body is supersonic while the flow in the base region is mixed supersonicsubsonic flow. Second, this flow is characterized by shock waveboundary layer interactions at the lip of the base region. Third, the flow is turbulent in the baseseparated region and highly transient in nature. There has been a long history of attempts to accurately describe this flow going back to the 1950s where integral models were used and continuing to the 2000s where sophisticated computation fluid dynamic models were used. However, none of these models have produced results that provide accurate descriptions of the flowfield.

Subject Categories:

  • Aerodynamics
  • Fluidics and Fluerics
  • Lasers and Masers
  • Guided Missile Trajectories, Accuracy and Ballistics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE