Design and Experimental Results for the S411 Airfoil

Abstract

A 14-percent-thick airfoil, the S411, 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 airfoil incorporates a 5-percent-chord tab. The two primary objectives of high maximum lift and low profile drag have been achieved. The constraint on the pitching moment has been exceeded; that on the airfoil thickness, satisfied. The airfoil exhibits a docile stall. Comparisons of the theoretical and experimental results generally show good agreement. Comparisons with the S406 airfoil confirm the achievement of the objectives.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 2010
Accession Number
ADA545987

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
  • Pressure Distribution
  • Pressure Gradients
  • Specifications
  • Standards
  • Static Pressure
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Software Engineering