Accession Number:

AD0818288

Title:

WIND TUNNEL INVESTIGATION TO DETERMINE AERODYNAMIC 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 on Phase 2

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• Homan, M. L.
• MacLanahan, Jr, D. A.

Report Date:

1967-08-01

Pagination or Media Count:

53.0

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 obtain aerodynamic force and moment data on the airborne vehicle during the abort sequence. Test results show that there was a reduction in magnitude of the pitching-moment and normal-force coefficients at all angles of attack as jet pressure ratio was increased. Thrust termination jet off to jet on resulted in an increase in the magnitude of both the yawing-moment and side-force coefficients at all angles of attack.

Descriptors:

• *LAUNCH VEHICLES
• ABORT
• AERODYNAMIC CHARACTERISTICS
• AERODYNAMIC LOADING
• ANGLE OF ATTACK
• INSTRUMENTATION
• LAUNCHING
• MOMENTS
• NOZZLE GAS FLOW
• PITCH(MOTION)
• ROCKET NOZZLES
• SEGMENTED ROCKET ENGINES
• SOLID PROPELLANT ROCKET ENGINES
• STABILITY
• SUPERSONIC CHARACTERISTICS
• THRUST TERMINATION SYSTEMS
• TRANSONIC CHARACTERISTICS
• WIND TUNNEL MODELS
• YAW

Subject Categories:

• Fluid Mechanics
• Ground Support Systems and Facilities for Space Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE