CFD Prediction of Magnus Effect in Subsonic to Supersonic Flight

Abstract

The aerodynamic coefficients of the 7-cal. U.S. Army-Navy Spinner Rocket were characterized using computational fluid dynamic (CFD) calculations and validated using archival experimental data. The static aerodynamic coefficients, roll-damping, and pitch-damping moments were accurately predicted by steady-state Reynolds-averaged Navier-Stokes (RANS) as well as unsteady hybrid RANS/large-eddy simulation (LES) CFD. The Magnus moment was overpredicted in the subsonic and transonic regime. Unsteady RANS/LES computations did not improve the prediction of Magnus moment at the lower Mach numbers. Both steady-state RANS and unsteady RANS/LES simulations resulted in similar predictions of all aerodynamic coefficients. Distributions of Magnus moment along the projectile body showed that the largest difference in Magnus moment between configurations and Mach numbers was in the last caliber of the projectile body.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2009
Accession Number
ADA508090

Entities

People

  • James DeSpirito

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Experimental Data
  • Flight
  • Fluid Dynamics
  • Fluid Flow
  • Large Eddy Simulation
  • Mach Number
  • Magnus Effect
  • Military Research
  • Physics Laboratories
  • Projectiles
  • Simulations
  • Steady State
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics