Design and Experimental Results for the S407 Airfoil

Abstract

An 11.43-percent-thick airfoil, the S407, intended for rotorcraft applications has been designed and analyzed theoretically and verified experimentally in The Pennsylvania State University Low-Speed, Low-Turbulence Wind Tunnel. The two primary objectives of high maximum lift and low profile drag have been achieved. The constraints on the pitching moment and the airfoil thickness have been satisfied. The airfoil exhibits a sharp stall, which does not meet the design objective. Comparisons of the theoretical and experimental results generally show good agreement.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 2010
Accession Number
ADA532304

Entities

People

  • Dan M. Somers
  • Mark D. Maughmer

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Fluid Dynamics
  • Laminar Flow
  • Leading Edges
  • Low Drag
  • Mach Number
  • Mechanical Properties
  • Mechanics
  • Pressure Distribution
  • Pressure Gradients
  • Standards
  • Static Pressure
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Mechanics and Fluid Dynamics.
  • Software Engineering