Design and Experimental Results for the S406 Airfoil

Abstract

A 14.25-percent-thick, natural-laminar-flow airfoil, the S406, 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 constraint on the airfoil thickness has been satisfied, but the one on the pitching moment has not. The airfoil exhibits a docile stall. 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
ADA532312

Entities

People

  • Dan M. Somers
  • Mark D. Maughmer

Tags

DTIC Thesaurus Topics

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

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.