WIND TUNNEL STUDY OF THE EFFECT OF MOL PROTUBERANCES ON STATIC-STABILITY AND PRESSURE DISTRIBUTION CHARACTERISTICS FOR SMALL-SCALE MODELS OF THE TITAN III/MOL LAUNCH VEHICLE

Abstract

Force, pressure, and acoustical data were obtained for the Titan III/ MOL (Manned Orbiting Laboratory) launch vehicle in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility. The primary objective of the test was to determine the effect of MOL protuberances on stability and axial-force coefficients and on surface pressure distributions. The force data were measured using three balances which sensed aerodynamic loads separately on the MOL-Gemini section, on the composition vehicle, and on one solid rocket motor. Mach number was varied from 0.60 to 3.00. Protuberance variations produced measurable changes in stability and axial-force characteristics for the MOL-Gemini section only. Surface pressures near the protuberances returned to protuberance-free trends within approximately 0.5-core diameters downstream of a protuberance trailing edge.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1967
Accession Number
AD0813324

Entities

People

  • Charles D. Riddle
  • Tommy O. Shadow

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Characteristics
  • Contracts
  • Diameters
  • Geometry
  • Government (Foreign)
  • Government Procurement
  • Governments
  • Launch Vehicles
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Rocket Engines
  • Test Facilities
  • Trailing Edges
  • Vehicles
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering.
  • Mathematics or Statistics

Technology Areas

  • Space
  • Space - Hall-Effect Thruster