An Aerodynamic Investigation of a Low Aspect Ratio Wing

Abstract

The study consisted of modeling and testing a high-speed, low aspect ratio flying wing (no conventional center body or fuselage) to determine its lift, drag, and static stability characteristics at Mach numbers of 0.70 to 0.86. Six different configurations of stabilizing fins were tested along with the basic finless configuration. Wind tunnel test results are presented in graphic and tabular form for use in further design studies.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1975
Accession Number
ADA021733

Entities

People

  • Leonard V. Mccommon

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Configurations
  • Air Force
  • Air Force Facilities
  • Aircrafts
  • Airfoils
  • All Wing Aircraft
  • Bending Stress
  • Boundary Layer
  • Center Of Gravity
  • Computer Programs
  • Engineering
  • Flow Visualization
  • Geometry
  • Materials Science
  • Measurement
  • Mechanics
  • Pressure Distribution
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.