EFFECT OF MACH NUMBER, REYNOLDS NUMBER, AND THICKNESS RATIO ON THE AERODYNAMIC CHARACTERISTICS OF NACA 63A-SERIES AIRFOIL SECTIONS.

Abstract

Force and moment data are presented from wind tunnel tests of two- dimensional symmetrical NACA 63A-Series airfoils of thickness ratios from 9 to 18 percent. The tests were conducted at Mach numbers ranging from M = .30 to M = .94 with Reynolds numbers varying from R = 2.0 X 1,000,000 to R = 9.5 X 1,000, 000 and at angles of attack as high as 29 degrees. Comparisons are made, wherever possible, with NACA tests of the same or similar airfoils. The transonic similarity rule is used to evaluate the consistency of the data.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1965
Accession Number
AD0619153

Entities

People

  • Norman B. Gorenberg
  • Oscar E. Sipe Jr.

Organizations

  • Lockheed Martin

Tags

Communities of Interest

  • Air Platforms
  • Human Systems
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airfoils
  • Airframes
  • Boundary Layer
  • Dynamic Pressure
  • Experimental Data
  • Fluid Dynamics
  • Free Stream
  • Helicopter Rotors
  • Helicopters
  • Mach Number
  • Pressure Distribution
  • Rotary Wing Aircraft
  • Test And Evaluation
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.