Subsonic Wind Tunnel Tests of a Canard-Control Missile Configuration in Pure Rolling Motion

Abstract

The description and run log of subsonic wind tunnel tests on a canard-control missile in pure rolling motion are presented. Test data for the body plus canard plus tail configuration (with 0-deg deflections) of the canard- control missile are shown. The nonlinear second-order differential equation of motion used in the global nonlinear least-squares analysis of the test data is discussed. Nonlinear aerodynamic coefficients extracted from the test data are presented and discussed. The results for the body plus canard plus tail configuration with 0-deg deflections showed that the linear roll damping moment coefficient increases slightly with the angle of attack up to about 20 deg, as predicted. However, at 30 deg the coefficient decreases significantly.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1977
Accession Number
ADA044957

Entities

People

  • Samuel R. Hardy

Organizations

  • Naval Surface Warfare Center Dahlgren Division

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Air Force
  • Air Force Facilities
  • Artillery
  • Cameras
  • Computer Programs
  • Differential Equations
  • Engineering
  • Equations
  • Exterior Ballistics
  • Marine Corps
  • Mechanical Engineering
  • Plastic Explosives
  • Subsonic Wind Tunnels
  • Test Equipment
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Control Systems Engineering.