Comparative Drag Measurements at Transonic Speeds of 6-Percent-Thick Airfoils of Symmetrical Double-Wedge and Circular-Arc Sections from Tests by the NACA Wing-Flow Method

Abstract

Results of comparative drag tests at zero lift on wings with symmetrical double-wedge section and symmetrical circular-arc section indicate that principal difference in drag characteristics is earlier drag increase with double-wedge section. Although double-wedge wing had somewhat higher drag throughout Mach number range tested, difference decreased with increasing Mach number after one set of drag increase of circular-arc section. At highest Mach number obtained, 1.10, drag coefficient for two sections was about the same.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Apr 08, 1947
Accession Number
ADA800545

Entities

People

  • N. S. Silsby

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamics
  • Aeronautical Laboratories
  • Aeronautics
  • Aircrafts
  • Airfoils
  • Airplanes
  • Aspect Ratio
  • Coefficients
  • Language
  • Mach Number
  • Measurement
  • Pressure Measurement
  • Reynolds Number
  • Translations
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.