Wind Tunnel Tests of a Large-Chord, Swept-Panel Model to Investigate Shock-Induced Separation Phenomena.

Abstract

The model had a chord of 3.5 feet with a streamwise airfoil section identical to that at 38.9 percent of the semispan of the C-141 wing, but had no taper or twist. Pressure distribution measurements were made through a range of angles of attack and Mach numbers for which data were available on the complete C-141 airplane from previous wind tunnel and flight tests. Fluctuating pressures at several chordwise locations near the shock were measured for a number of test conditions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1969
Accession Number
AD0861041

Entities

People

  • E. Stanewsky
  • J. F. Cahill

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airplanes
  • Fixed Wing Aircraft
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Dynamics.