1987-10-01

Experimental Flowfield Measurements of a Nose Cavity Configuration 871880

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.

SAE MOBILUS

Subscribers can view annotate, and download all of SAE's content. Learn More »

Access SAE MOBILUS »

Members save up to 43% off list price.
Login to see discount.
Special Offer: Purchase more aerospace standards and aerospace material specifications and save! AeroPaks off a customized subscription plan that lets you pay for just the documents that you need, when you need them.
X