Accession Number:

AD0801873

Title:

WIND TUNNEL INVESTIGATION TO DETERMINE STATIC STABILITY AND PRESSURE DISTRIBUTION CHARACTERISTICS OF SMALL-SCALE MODELS OF THE TITAN III/MOL LAUNCH CONFIGURATION AT MACH NUMBERS FROM 0.60 TO 3.10

Descriptive Note:

Technical rept. 1 Jun-7 Jul 1966

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Report Date:

1966-11-01

Pagination or Media Count:

122.0

Abstract:

Models of the Titan 3 Manned Orbiting Laboratory MOL launch vehicle were tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.60 to 3.10 to determine pressure and acoustical characteristics for structural design confirmation and to obtain force balance data for flight control and trajectory analysis. A calibration cone was also tested to evaluate tunnel background noise in the Titan 3 MOL acoustical data. Force data were obtained by using four internal balances to sense separate aerodynamic loads on the composite model and on the MOL, MOL-Gemini, and solid rocket motors SRM sections. Modification of the SRM noses to a less blunt configuration resulted in a reduction of composite and SRM axial load and tended to position the composite longitudinal neutral point at a more forward location. Lateral neutral point for the composite model exhibited a maximum travel of 2.6 core diameters for the 0.60 and 3.10 Mach number range whereas the longitudinal neutral-point travel was 1.0 diameters. The acoustical results are not presented in this report.

Subject Categories:

  • Spacecraft Trajectories and Reentry
  • Ground Support Systems and Facilities for Space Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE