Supersonic Wind Tunnel Measurements of Static and Magnus Aerodynamic Coefficients for Projectile Shapes with Tangent and Secant Ogive Noses

Abstract

Wind tunnel tests have been conducted for a series of projectile configurations. The shapes tested include a three caliber secant ogive nose and three caliber tangent ogive nose configuration. The overall model length was fixed at 6 calibers for all configurations tested. Static and Magnus aerodynamic coefficient data were obtained at Mach numbers 2.0, 3.0 and 4.0 for angles of attack up to 10.0 deg. The data are presented in graphical form along with tabulations of the summary data. The tangent ogive nose produced a slight increase in the Magnus moment coefficient when compared to similar secant ogive configurations. The boattail configuration, when compared to the cylinder shapes, was found to increase the Magnus moment; however, this effect was shown to decrease with increasing Mach number.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1980
Accession Number
ADA083297

Entities

People

  • Charles J. Nietubicz
  • Klaus O. Opalka

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Bodies
  • Boundary Layer
  • Classification
  • Coefficients
  • Data Acquisition
  • Dynamic Pressure
  • Fluid Dynamics
  • Fluid Mechanics
  • Free Stream
  • Mach Number
  • Measurement
  • Security
  • Supersonic Wind Tunnels
  • Three Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Mechanical Engineering/Mechanics of Materials.
  • ballistics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow