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Title
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Investigation Of Escape Capsule Systems For Multi-place Aircraft. Part II: Preliminary Design And wind Tunnel Testing Of An Individual Escape Capsule
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Date
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1961
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Index Abstract
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Not Available
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Photo Quality
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Incomplete
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Report Number
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WADC TR 57-329 Part 2
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Creator
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Milhoan, F. M.
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Vorachek, J. J.
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D'Allura, J.
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Corporate Author
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Goodyear Aircraft Corporation
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Laboratory
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Flight Dynamics Laboratory
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Extent
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282
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Identifier
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AD0273626
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Access Rights
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OTS
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Distribution Classification
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1
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Contract
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AF 33(616)-5017
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DoD Task
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13438
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DTIC Record Exists
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No
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Special Scanning Requirements
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fold out pages
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Abstract
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Design and dynamic model and wind tunnel model testing is reported for an individual escape capsule as part of a program for the investigation of escape capsule systems for a hypothetical multi-place aircraft. The capsule provides safe escape over an aircraft performance envelope having a maximum equivalent airspeed of 800 knots through an altitude range from sea level to 55,000 ft and a Mach number of 4.0 from 55,000 to 100,000 ft with a flight duration of 30 hr. The preliminary design is described. Results from stress and weight analyses are included. A preliminary performance and stability analysis of 3 capsule stabilization systems, including fins, boom-balloon configurations, and trailing drag bodies, was made, and a system comprised of a variable sized inflatable drag body was selected and further analyzed. Data used for the analysis was obtained from quarter-scale model freeflight tests and transonic and supersonic wind tunnel tests from Mach 0.5 to 3.0. Graphical results from the wind tunnel tests are included.
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Report Availability
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Full text available by request
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Date Issued
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1961-12
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DoD Project
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1362 - Crew Escape for Flight Vehicles
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Type
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report
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Provenance
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Lockheed Martin Missiles & Fire Control