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

Abstract

A 0.03-scale model of the Titan III/Manned 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.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1967
Accession Number
AD0816611

Entities

People

  • D. A. Maclanahan Jr.
  • M. L. Homan

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Coefficients
  • Export Controls
  • Exports
  • Government (Foreign)
  • Governments
  • Instrumentation
  • Launch Vehicles
  • Mach Number
  • Measurement
  • Models
  • Pressure Distribution
  • Scale Models
  • Sequences
  • Solid Propellants
  • Test Facilities
  • Vehicles
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Test and Evaluation
  • Missile Defense Systems.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster