Aerodynamic Characteristics of Sounding Rockets with Attached Gerdian Condensers from Mach 2.5to 8,

摘要

An investigation has been conducted in the 4in x 4in 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 2.5to 8. The angle of attack was varied from about -2.5degrees to 2.5degrees 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)