MOL Fluid Dynamics Test Pretest Report. MOL Protuberance Heating Wind Tunnel Model. Sequence Number B334. Data Item Number UT-135

Abstract

The report outlines objectives and test requirements for wind tunnel testing of several protuberances unique to the MOL vehicle. An important feature of the testing program is the investigation of heating rates on protuberances wholly or partially submerged in a boundary layer. In order to achieve a thick boundary layer, the models are mounted on the floor of the tunnel. A thin, instrumented plate replaces the ordinary tunnel floor plates, in order to investigate the disturbances caused by the protuberances on the surrounding flow fields. A wake heating region of at least 35 inches will be available. The protuberance models and the metric floor plate are constructed of thin nickel shells 1/16 inch thick. Heat transfer data will be collected by applying thin skin temperature response techniques. The models will be tested at Mach numbers of 2.5, 3.0, 3.5, 4.0, 4.5, and 5.0 and unit Reynolds number will be varied to the limits of the tunnel and structural limits of the models.

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Document Details

Document Type
Technical Report
Publication Date
Feb 26, 1968
Accession Number
AD0856515

Entities

Organizations

  • Douglas

Tags

Communities of Interest

  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Convection
  • Data Reduction
  • Design Criteria
  • Dynamic Pressure
  • Equations
  • Fluid Dynamics
  • Heat Transfer
  • Materials
  • Physics Laboratories
  • Pressure Distribution
  • Reynolds Number
  • Temperature Gradients
  • Test Facilities
  • Wind Tunnel Models
  • Wind Tunnels

Readers

  • Aerospace Test and Evaluation
  • Fluid Mechanics and Fluid Dynamics.
  • Structural Dynamics.