Accession Number : AD0717193

Title :   Critical Evaluation of a Nonuniform Flow Sonic Boom Reduction Concept.

Descriptive Note : Technical rept. Oct 68-Jul 69,

Corporate Author : AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Weeks,Thomas M.

Report Date : SEP 1970

Pagination or Media Count : 40

Abstract : An investigation was made of a 'nonuniform flow field' sonic boom elimination device. The two-dimensional flow field consists of a slit jet impinging on an inclined fat plate airfoil. The report presents independent analyses of the problem as well as a critique of the analysis. The major finding is that one can expect no more than a 10% reduction in the strength of the leading edge shock wave at a thousand chord lengths from the plate when compared to the corresponding case without jet flow (same chord and lower surface pressure). Under identical conditions, a 20% reduction is found. (Author)

Descriptors :   (*SONIC BOOM, REDUCTION), TWO DIMENSIONAL FLOW, FLOW FIELDS, JETS, FLAT PLATE MODELS, LEADING EDGES, INTERACTIONS

Subject Categories : Acoustics

Distribution Statement : APPROVED FOR PUBLIC RELEASE