SOME SPHERE DRAG MEASUREMENTS IN LOW DENSITY SHOCK TUNNEL FLOWS

Abstract

The free flight technique was extended to low density flows to measure sphere drag at approximately Mach 15 over a free stream Knudsen number range of .0027 to .25. Comparison of the data obtained with those of other investigators indicates that: (a) The free flight technique is useful for shock tunnel measurements of aero dynamic forces in non-continuum flows. (b) There is little to choose from between free stream Knudsen and Reynold's Numbers, and Reynold's Number (at conditions behind normal shock) as a correlating variable for experimental sphere drag coefficients. (c) The parameter CD - CDi/CDfm - CDi yields a useful correlation of sphere drag over a wide range of Mach numbers, Reynolds number and wall Temperatures.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1963
Accession Number
AD0409517

Entities

People

  • R. E. Geiger

Organizations

  • General Electric

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Coefficients
  • Experimental Data
  • Flow
  • Fluid Dynamics
  • Free Flight
  • Free Stream
  • Ignition Systems
  • Knudsen Number
  • Low Density
  • Mach Number
  • Mean Free Path
  • Measurement
  • Physics Laboratories
  • Reynolds Number
  • Shock Tunnels
  • Space Sciences

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.