INVESTIGATION OF A BOUNDARY LAYER ATTENUATION SYSTEM. PART 1. LOW OVERPRESSURES.
Abstract
An air blast wave attenuation system for use with hardened structures and air entrainment systems was investigated, but analysis of the system which depends upon the relationship between choked flow and non-steady supersonic boundary layer formation is not so advanced that it can be completely described. However, an empirical confirmation is included and the feasibility of such an attenuator was verified experimentally. Results from shock tube experiments show that shock front attenuation increased nominally as the incident shock pressure was increased. In addition, significant attenuation was noted in the flow-field behind the shock front. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1969
- Accession Number
- AD0688419
Entities
People
- Dana Williams
Organizations
- Naval Facilities Engineering Service Center