Accession Number:

AD0816611

Title:

WIND TUNNEL INVESTIGATION TO DETERMINE PRESSURE DISTRIBUTION CHARACTERISTICS OF A 0.03-SCALE MODEL OF THE TITAN III/MOL LAUNCH CONFIGURATION DURING THE ABORT SEQUENCE AT MACH NUMBERS FROM 0.60 TO 3.00

Descriptive Note:

Technical rept. 13 Mar-24 Apr 1967

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1967-07-01

Pagination or Media Count:

39.0

Abstract:

A 0.03-scale model of the Titan IIIManned Orbiting Laboratory MOL launch vehicle was tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.6 to 3.0 to determine pressure distributions on the airborne vehicle during the abort sequence. Test results show that the jet, simulating thrust termination, forces the solid-propellant motor induced normal shock forward. Disturbances caused by the jet produce an increase in the pressure coefficient in the region ahead of the jet and a decrease in the pressure coefficient in the region aft of the jet.

Subject Categories:

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

Distribution Statement:

APPROVED FOR PUBLIC RELEASE