Investigation of Plume Effects on the Stability Characteristics of a Body of Revolution with Various Fin Configurations at Transonic Speeds
Abstract
A transonic wind tunnel test was performed in the Calspan Corporation 8-Foot Transonic Wind Tunnel on a missile model with tail fins in the presence of a simulated jet plume. The test was conducted during February, 1974. The purpose of the test was to establish a correlation between the thrust level and missile longitudinal stability, and to assess the effectiveness of locating stabilizing fins forward of the model base as a means of alleviating adverse plume effects. This was the second series of tests performed with this model at Calspan. The results of the earlier test, which also included a canard effectiveness study, were previously reported. The test was conducted over a Mach number range from 0.40 to 1.25 at a condition corresponding to a wind-off static pressure of 0.5 atmospheres. Model angle of attack was varied from -4 to 12 degrees.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1974
- Accession Number
- AD0782208
Entities
People
- R. E. De Kuyper
Organizations
- Calspan