Accession Number : AD0688419

Title :   INVESTIGATION OF A BOUNDARY LAYER ATTENUATION SYSTEM. PART 1. LOW OVERPRESSURES.

Descriptive Note : Technical rept. Jul 67-Jun 68,

Corporate Author : NAVAL CIVIL ENGINEERING LAB PORT HUENEME CALIF

Personal Author(s) : Williams,D. E.

Report Date : MAY 1969

Pagination or Media Count : 32

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)

Descriptors :   (*SHELTERS, NUCLEAR EXPLOSIONS), (*DUCTS, SHOCK WAVES), BOUNDARY LAYER, ATTENUATION, PROTECTION, BLAST, FLOW FIELDS, TEST METHODS, THEORY, CORRELATION TECHNIQUES, SHOCK TUBES

Subject Categories : Structural Engineering and Building Technology

Distribution Statement : APPROVED FOR PUBLIC RELEASE