Parafoil Wind Tunnel Tests

Abstract

Extensive parafoil wind tunnel tests were carried out. Parafoil model sizes ranged from .09 sq ft to 147 sq ft and parafoil aspect ratios ranged from .5 to 3.0. The wind tunnel test velocities ranged from approximately 20 ft per second to over 60 ft per second. The aerodynamic stability coefficients were measured. The parafoil remained self inflated and rigid over a range of angle from -10 to 80 deg and revealed no stall characteristics Maximum lift coefficients from 0.751 to 1.005 were measured for parafoils of different aspect ratio. Maximum lift to drag ratios ranging from 1.83 to 6.40 were measured for the various parafoil designs. The various wind tunnel tests confirm both the static and the dynamic stability of the parafoil in pitch yaw, and roll. The results of these investigations are consolidated in the report by summary plots and special presentations.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1971
Accession Number
AD0731564

Entities

People

  • John D. Nicolaides

Organizations

  • University of Notre Dame

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Aerodynamic Stability
  • Aircraft Equipment
  • Airplanes
  • Bearings
  • Cameras
  • Engineering
  • Flight
  • Flow Fields
  • Fluid Dynamics
  • Free Flight
  • Geometry
  • Measurement
  • Mechanical Engineering
  • Vehicle Equipment
  • Wind Tunnels

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.
  • Marine Hydrodynamics