An F-104B airplane was modified to investigate the drag and stability characteristics of a ballute decelerator in the wake of an asymmetrical airplane. Decelerator deployments were initiated at a Mach number of 1.3 and an altitude of 15,240 meters (50,000 feet) and terminated when the airplane had decelerated to a Mach number of 0.5. The flight tests indicated that the decelerator had a short inflation time with relatively small opening forces. The drag levels attained with the subject decelerator were less than those obtained with other high-speed decelerators behind a symmetrical tow vehicle. The ballute demonstrated good stability characteristics behind the testbed airplane. (Author)
Performance of a Ballute Decelerator Towed Behind a Jet Airplane
1973
26 pages
Report
No indication
English
LOW DENSITY SUPERSONIC DECELERATOR BALLUTE DESIGN AND PACKING
British Library Conference Proceedings | 2015
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