Accession Number:

AD0754907

Title:

Parafoil Powered Flight Performance

Descriptive Note:

Final rept.

Corporate Author:

NOTRE DAME UNIV IN DEPT OF AEROSPACE AND MECHANICAL ENGINEERING

Personal Author(s):

Report Date:

1972-01-01

Pagination or Media Count:

116.0

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.

Subject Categories:

  • Gliders and Parachutes

Distribution Statement:

APPROVED FOR PUBLIC RELEASE