Aerothermodynamic Study of a Generic EFP Configuration
Abstract
The present study addresses the aerodynamics of a generic explosively formed penetrator body in Mach 6 hypersonic flight at sea level. As a first study of this type, the shape of the body is held fixed, and the flow field is resolved by applying state-of-the-art eddy simulation techniques in conjunction with a hybrid shock-turbulence capturing algorithm. Air is treated as a mixture of nitrogen and oxygen, and the governing equations are closed by a modern compressible turbulence closure term. Pressure is determined by using the thermally perfect gas equation of state applied to each species. The generic body also possesses an interior cavity. The flow field is captured both inside and outside of the body. Since aerodynamic breakup is of great concern, the distribution of temperature is determined on the body surfaces as well as temperature gradients based upon adiabatic wall boundary conditions. Also, the structure of the flow field is examined as is the time required for stationarity. These factors have an effect on flight stability.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 2010
- Accession Number
- ADA519896
Entities
People
- Douglas V. Nance
- Kirk J. Vanden
Organizations
- Air Force Research Laboratory