An Experimental Investigation of the Effects of Rocket Plume Simulators on the Radial and Longitudinal Pressure Distribution of a Sting Mounted Body of Revolution at Transonic Mach Numbers
Abstract
Experimental aerodynamic investigations were conducted at the Cornell Aeronautical Laboratory (CAL) transonic wind tunnel to determine the effects of several rocket plume simulators on the pressure distribution of a body of revolution. These tests were conducted during September, 1971, on a sting supported model and were extensions of earlier (August 1970) tests on similar strut supported models. Therefore, these data can also be utilized to determine the effects of strut mounting on data validity. Local surface pressure data were recorded over an angle of attack range of plus or minus 2 degrees at Mach numbers of 0.9, 1.0 and 1.2 on a four-caliber tangent ogive nose with a cylindrical, a boattailed, and a flared afterbody and on the cylindrical afterbody with either a solid disc or a perpendicular (normal) jet flow acting as plume simulators.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1973
- Accession Number
- AD0763904
Entities
People
- James R. Burt Jr.
Organizations
- Stellantis North America (formerly Chrysler)