Pressure Measurements on the Interior Surface of a 75mm Tubular Projectile at Mach 4
Abstract
Wind tunnel pressure measurements were obtained on the interior surface of a solid-fuel-ramjet, tank-gun, training projectile. All data were obtained at Mach 4.03, a free-stream Reynolds number of approximately 76.6 million per meter and at zero degrees angle of attack. The tests were preliminary in nature and were not intended to simulate actual flight conditions. The projectile was not spinning and there was no burning of fuel nor was there any simulated burning by gas injection. The injector hole diameter, upstream from the fuel section, was varied and some injectors were notched to form vortex generators. Two conventional nozzles were tested and a third nozzle was equipped with a butterfly valve so that pressure distributions could be obtained at various levels of flow restriction. Schlieren photography was available to help determine if the flow was choked by showing an attached or detached shock at the inlet leading edge. Some apparent critical flow behavior is indicated by drastic changes in pressure distribution for modest changes in internal geometry.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1988
- Accession Number
- ADA202410
Entities
People
- Carl A. Trexler
- Lyle D. Kayser
- Rao J. Yalamanchili
Organizations
- Ballistic Research Laboratory