Aerodynamic Characteristics of Sounding Rockets with Attached Gerdian Condensers from Mach 2.5 to 8,
Abstract
An investigation has been conducted in the 4 in x 4 in supersonic wind tunnel at Boston University to determine the aerodynamic characteristics of a Tomahawk sounding rocket with attached gerdian condensers for a flight region of Mach 2.5 to 8. The angle of attack was varied from about -2.5 degrees to 2.5 degrees and zero sideslip was maintained. Results are presented showing the variation of the longitudinal stability with Mach number and roll angle of the condensers. No unstable configuration was found within the testing range of the present investigation. The aerodynamic forces were also determined. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1974
- Accession Number
- AD0780544
Entities
People
- Daniel G. Udelson
- Paul Soohoo
- Rocco Girolamo
Organizations
- Boston University