AN EXPERIMENTAL INVESTIGATION OF THE ZERO-LIFT-DRAG CHARACTERISTICS OF SYMMETRICAL BLUNT-TRAILING-EDGE AIRFOILS AT MACH NUMBERS FROM 2.7 TO 5.0

Abstract

The zero-lift-drag characteristics of nine symmetrical airfoils were investigated experimentally at Mach numbers from 2.7 to 5.0 and Reynolds numbers (based on the chord) from 0.35 million to 3.63 million. Eight of these airfoils had blunt trailing edges and were designed to have minimum pressure drag at Mach number of 3 or 5 for a given torsional rigidity or a given bending strength. The ninth airfoil was a conventional biconvex section having a torsional rigidity equal to that of three of the minimum-drag airfoils. Section thickness ratios varied from 3.74 to 6.10 percent.

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Document Details

Document Type
Technical Report
Publication Date
Apr 29, 1953
Accession Number
AD0009131

Entities

People

  • Clarence A. Syvertson
  • Hermilo R. Gloria

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Base Pressure
  • Bodies
  • Boundary Layer
  • Fineness Ratio
  • Free Stream
  • Laminar Boundary Layer
  • Mach Number
  • Measurement
  • Moment Of Inertia
  • Pressure Distribution
  • Pressure Gages
  • Pressure Measurement
  • Reynolds Number
  • Skin Friction
  • Trailing Edges
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Solar Physics