Experimental Flowfield Measurements of a Nose Cavity Configuration The BDM Corporation

Format:

Conference/Event

Author/Creator:

Huebner, Lawrence D., author.

Conference Name:

Aerospace Technology Conference & Exposition (1987-10-05 : Long Beach, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1987

Summary:

A wind tunnel test was conducted to experimentally investigate the fluid flow phenomena that resulted when a nose cavity configuration was introduced into a hypersonic environment. This experiment served two purposes: First, to study the nature of the bow shock and anticipated reduced thermal characteristics and uniform pressures at the cavity base, and second, to verify analytical predictions that were performed on this concept prior to the test.The results indicate that the bow shock would oscillate with low amplitude at the acoustic frequency of the cavity. The heat transfer rate at the cavity base was reduced compared to the rim of the nose. Correlations of the wind tunnel results were made with computational analysis and previous wind tunnel results

Notes:

Vendor supplied data

Publisher Number:

871880

Access Restriction:

Restricted for use by site license