Navier-Stokes Computational Study of the Influence of Shell Geometry on the Magnus Effect at Supersonic Speeds

Abstract

Recent papers have reported the application of the thin-layer Parabolized Navier-Stokes (PNS) computational technique to predict the flow over spinning shell at supersonic speeds. This paper reports the results of a computational study using thin layer Navier-Stokes codes to examine the effects of shell nose tip and afterbody geometry. The geometries considered include sharp, hemisphere cap, and flattened nose configurations and a parametric variation of the boattail shape. The results are presented primarily as the aerodynamic coefficients versus Mach number of 1.5 less than M less than 5. The Magnus effect is shown to be strongly influenced by nose bluntness as well as the geometry of the shell afterbody.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1983
Accession Number
ADA130630

Entities

People

  • Bernard Guidos
  • Charles J. Nietubicz
  • Donald C. Mylin
  • Walter B. Sturek

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Bodies
  • Bodies Of Revolution
  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Hemispheres
  • Mach Number
  • Magnus Effect
  • Measurement
  • Nose Tips
  • Noses
  • Viscous Flow
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers