The Drag of Finite-Length Cylinders Determined From Flight Tests at High Reynolds Numbers for a Mach Number Range From 0.5 to 1.3

Abstract

Results of a free-flight investigation to determine the drag of circular, finite-length cylinders are presented for a Mach number range from about O.5 to 1.5. Fineness ratios of the cylinders tested were 50, and 60. Results of previous experimental tests of circular cylinders having infinite fineness ratios are included in this paper for comparison. For supersonic speeds, the drag of circular cylinders is largely independent of fineness ratio and Reynolds number. At subsonic Mach numbers, the drag of finite-length cylinders (fineness ratios of about 60 and below) increases as their fineness ratios increase.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1953
Accession Number
ADA381079

Entities

People

  • Clement J. Welsh

Organizations

  • Naval Air Station Patuxent River

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Aircraft Rockets
  • Aircrafts
  • Bodies
  • Booster Rocket Engines
  • Coefficients
  • Diameters
  • Drag
  • Fineness Ratio
  • Flight
  • Free Flight
  • Mach Number
  • Reynolds Number
  • Three Dimensional
  • Turbulent Flow
  • Unmanned Aerial Vehicles

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow