Transonic Scaling Effect on a Quasi, Two-Dimensional C-141 Airfoil Model

Abstract

The transonic scaling effect of shock wave/boundary-layer interaction on a quasi, two-dimensional C-141 airfoil was investigated. Data were obtained from the AEDC Propulsion Wind Tunnel Facility Aerodynamic Wind Tunnel (4T) and Propulsion Wind Tunnel (16T) and from the NASA Marshall Space FLIGHT Center High Reynolds Number Tunnel with 6-in.- and 24-in.-chord airfoils for a range 0.70 to 0.85. In addition to the investigation of the effect of Reynolds number on the airfoil pressure distribution, the effect of fixed boundary-layer transition was evaluated using grit-type transition strips on the airfoil surface. The significant parameters affecting the shock wave/boundary-layer interaction are identified. The data indicate that simulation of higher Reynolds number data on the C-141 airfoil model is feasible by use of a fixed-boundary-layer-transition strip.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1973
Accession Number
AD0762285

Entities

People

  • C. F. Lo
  • W. E. Carleton

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Boundary Layer
  • Boundary Layer Transition
  • Flow
  • Flow Fields
  • Instrumentation
  • Layers
  • Mach Number
  • Pressure Distribution
  • Shock Waves
  • Simulations
  • Space Flight
  • Supercritical Flow
  • Test Facilities
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering.
  • Combustion Dynamics and Shock Wave Physics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster