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20141009010000.0 |
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040507s1970 dcua bt f000 0 eng d |
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‡aCHVBK
‡b12303549X
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‡asdr-uiuc6401280
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‡a(OCoLC)249206849
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‡aGyGoGBV
‡erakwb
‡bger
‡cGBVCP
‡dFER
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‡aUIUU
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‡aNAS 1.14:D-5796
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‡aTL753
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‡aEckstrom, Clinton V.
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‡aHigh-altitude flight test of a 40-foot-diameter (12.2-meter) ringsail parachute at a deployment Mach number of 2.95 /
‡cby Clinton V. Eckstrom.
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‡aWashington, DC :
‡bNational Aeronautics and Space Administration,
‡c1970.
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‡a[i], 49 p. :
‡bill. ;
‡c26 cm.
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‡aNASA technical note ;
‡vNASA TN D-5796
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‡a"L-1077."
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‡a"L-7002."
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‡a"NASA TN D-5796."
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‡a"June 1970."
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‡aIncludes bibliographical references (p. 15).
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‡aA 40-foot-nominal-diameter (12.2-meter) modified ringsail parachute was flight tested as part of the NASA Supersonic High Altitude Parachute Experiment (SHAPE) program. The 41-pound (18.6-kg) test parachute system was deployed from a 239.5-pound (108.6-kg) instrumented payload by means of a deployment mortar when the payload was at a Mach number of 2.95 and a free-stream dynamic pressure of 9.2 lb/sq ft (440 N/m²). The parachute deployed properly with the canopy inflating to a near full open condition followed immediately by a partial collapse of the canopy and subsequent oscillations of the frontal area until the system had decelerated to a Mach number of about 1.5. The parachute then attained an inflated shape that provided full drag area. During the supersonic part of the test, the average axial-force coefficient C A ,₀ varied from a minimum of about 0.24 at a Mach number of 2.7 to a maximum of 0.54 at a Mach number of 1.1. During descent under subsonic conditions, the average effective drag coefficient was 0.62 and parachute-payload oscillation angles averaged about ±10⁰ with excursions to ±20⁰.--P. [i].
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‡aAlso available online in PDF and Quicktime movie format from NASA Technical Reports Server Web site.
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‡aSponsored by the National Aeronautics and Space Administration (NASA); performed by the NASA Langley Research Center under
‡h709-12-00-01.
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‡aMode of access: Internet.
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‡aParachutes
‡xTesting.
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‡aParachutes
‡xAerodynamics.
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‡aUnited States.
‡bNational Aeronautics and Space Administration.
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‡aLangley Research Center.
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‡a011443922
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‡a20101109111634.0
‡b20141009010000.0
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‡a20141112165512.0
‡b2023-03-14T18:33:15Z
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‡aSDR-UIUC
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‡lloader.pl-003-020
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‡bUIU
‡cUIUC
‡d20230314
‡sgoogle
‡uuiug.30112106780502
‡y1970
‡rpd
‡qbib
‡tUS fed doc
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