The effects of design parameters and local flow fields on the performance of hyperflo supersonic parachutes and high dynamic pressure parachute concepts /
Leland W. Sims.

Description

Main Author

Sims, Leland W.

Related Names

Air Force Flight Dynamics Laboratory (U.S.)

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965.

Subjects

Supersonic planes
Aircraft survival equipment.
Parachutes > Parachutes / Design and construction.

Summary

Wake flow field surveys were conducted in the wind tunnel behind several side strut mounted forebodies in the Mach number range from 2 to 5. Studies of the effects of design parameters on Hyperflo supersonic parachutes, and of high dynamic pressure parachute configurations deployed in such wakes were performed. Wake pressure distributions indicated an asymmetry due to the forebody support structure, and a disturbance to the flow field which emanates from the support structure. The latter was most pronounced at Mach numbers above 3. Modification to the wake caused by an air bleed into the forebody base was also indicated. Normal, but higher than predicted axial wake Mach number distributions were found to exist in the forebody wakes. Hyperflo tests at Mach numbers 5 to 5.5 showed abnormally large parachute oscillations with models located at large downstream positions aft of the forebodies. The effects of Hyperflo design parameters and forebody type on model performance are only qualitatively indicated by the tests conducted. (Author).

Note

"October 1965."

Physical Description

xvi, 195 pages : illustrations ; 28 cm.

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