Wind Tunnel Fluctuating Pressure Tests on a 10 Percent Scale Model of the Gemini B Spacecraft at Ames Unitary Plan Wind Tunnel.
Abstract
A 10 percent scale model of the Gemini B reentry module and adapter was tested in conjunction with the Laboratory Vehicle. The test encompassed a Mach number range of 0.6 through 2.4, an angle-of-attack range -6 through 6 degrees and an angle-of-sideslip range -4 through 10 degrees. The purpose of the test was to obtain wideband buffeting pressure data needed to perform structural response analyses of the Gemini B adapter and laboratory unpressurized forward skirt. Model fluctuating pressure, schlieren, and tunnel pressure data were recorded. Overall model sound pressure levels (RMS) and tunnel conditions are tabulated in the report for each data point taken. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 13, 1967
- Accession Number
- AD0856895
Entities
People
- J. E. Gregoire