Missile Base Flow: Hybrid RANS/LES Computational Fluid Dynamics Comparisons to Measurements
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 base/separated 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 supersonic/subsonic flow. Second, this flow is characterized by shock wave/boundary layer interactions at the lip of the base region. Third, the flow is turbulent in the base/separated 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 2008
- Accession Number
- ADA503640
Entities
People
- B. J. Walker
- C. D. Mikkelsen
- K. D. Kennedy