Theoretical Supersonic Lift and Drag Characteristics of Symmetrical Wedge-Shape Airfoil Sections as Affected by Sweepback Outside the Mach Cone

Abstract

Report extends work of Busemann using component theory and simplified method for determining pressure distribution around thin, sharp-nosed airfoils at superonsic speeds. Results indicate that increasing sweepback at constant-stream Mach increases lift/pressure drag and lift/total drag ratios, provided thickness ratio decreases, increases slop of lift curve, and decrease minimum drag coefficient. Section lift coefficient for maximum lift/pressure drag and lift/total drag ratios decreases with increase in free stream Mach.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1947
Accession Number
ADA800557

Entities

People

  • Edward N. Bowen Jr.
  • H. R. Ivey

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamics
  • Aeronautical Laboratories
  • Aeronautics
  • Airfoils
  • Coefficients
  • Drag
  • Dynamic Pressure
  • Flow
  • Free Stream
  • Friction
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Skin Friction
  • Static Pressure
  • Sweptback Wings
  • Thickness

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics