Variable Camber Wing

Abstract

The initial series of wind tunnel tests which were designed to demonstrate the aerodynamic advantages of an advanced technology variable camber wing have been completed. These tests were conducted during twenty-four shifts of occupancy time at the NASA Ames 14-foot transonic wind tunnel between May 21 and June 15, 1973. The configurations tested consisted of the basic F-8, the F-8 with an advanced technology wing, the advanced wing with simple hinged leading and trailing edge flaps and various combinations of smooth, curved variable camber flaps. A summary of the test configurations and test conditions is presented.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1973
Accession Number
AD0911543

Entities

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Camber
  • Control Systems
  • Failure Mode And Effect Analysis
  • High Angles
  • Leading Edge Flaps
  • Leading Edges
  • Pressure Distribution
  • Supersonic Wind Tunnels
  • Surfaces
  • Test And Evaluation
  • Trailing Edges
  • Transonic Wind Tunnels
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels
  • Wing Boxes

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Materials Science