Parafoil Powered Flight Performance

Abstract

The predicted flight performance of a powered parafoil flight vehicle is calculated from solutions which are obtained from the parafoil equations of motion. Flight vehicle total weights of 350, 400, 500, and 540 pounds are considered. Parafoil wing areas of 200 square feet and 400 square feet are considered. Wing loadings include .875, 1.0, 1.25, 1.35, 1.75, 2.0, and 2.7 pounds per square foot. Steady state flight trim angles of attack cover a range from -6 degrees to +80 degrees. The flight performance analyses include level flight, climbing flight, and descending flight. The computed flight parameters include the total velocity, the rate of climb (sink), the angle of climb (descent), and the horsepower required for the type of flight under consideration.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1972
Accession Number
AD0754907

Entities

People

  • John D. Nicolaides

Organizations

  • University of Notre Dame

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Altitude
  • Aspect Ratio
  • Control Systems
  • Engineering
  • Engineers
  • Equations Of Motion
  • Flight Paths
  • Free Flight
  • Measurement
  • Mechanical Engineering
  • Sea Level
  • Test Vehicles
  • Vehicle Equipment

Readers

  • Aerodynamics/Aeronautics.