Drag Characteristics of Rectangular and Swept-Back NACA 65-009 Airfoils Having Various Aspect Ratios as Determined by Flight Tests at Supersonic Speeds

Abstract

Tests on rocket-propelled bodies carrying wings of aspect ratios between 3.8 and 5.0 at various swept-back angles show that drag coefficient decreased as swept-back angle increased and that this decrease becomes more pronounced with larger aspect ratios. For Mach numbers greater than value at which Mach line lies ahead of leading edge, drag coefficient decreased with decrease in aspect ratio. Aspect ratio effect diminished with increased swept-back angle. At 45 degrees only negligible drag coefficient changes resulted between aspect ratios of 1.5 and 5.0. Data substantiate theoretical calculations.

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Document Details

Document Type
Technical Report
Publication Date
Apr 22, 1947
Accession Number
ADA800546

Entities

People

  • Robert L. Nelson
  • Warren A. Tucker

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Accuracy
  • Aeronautical Laboratories
  • Aeronautics
  • Aircrafts
  • Airfoils
  • Aspect Ratio
  • Bodies
  • Boundary Layer
  • Coefficients
  • Language
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Measurement
  • Static Pressure
  • Translations

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics