Analysis of Experiments on the Effects of Jet Plumes on Pressure Distribution over a Cylindrical Afterbody at Transonic Speeds.
Abstract
The objective of the present investigation was to obtain experimentally, the effects of various jet plume parameters on afterbody pressure distributions and to partially validate the Korst modeling procedure. Analysis of the experimental results and supplemental calculations made by the method of characteristics show that the approximate theory used by Korst, gives a good estimate of the plume shape for nozzle exist Mach number of 2.0 and below. For nozzle exit Mach numbers much in excess of 2.0, it appears desirable to include the effect of the nozzle wall boundary layer on plume shape. In addition, afterbody pressure distributions produced by a series of nozzles designed to produce the same plume shape, but with different values of the plume pliability parameter, have been compared with results from a solid plume simulator. In general, the solid plume simulator produces results that agree with the nozzles with the higher values of the plume pliability parameter at zero degrees angle of attack. The correlation deteriorates significantly, however, at five degrees angle of attack. Also, afterbody pressure distributions from model tests on the ZAP rocket motor are presented for future correlation with prototype results. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1980
- Accession Number
- ADA081647
Entities
People
- Joseph P. Nenni
Organizations
- Calspan