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collection:
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nasa new
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nasa new
collection
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mediatype:
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texts
mediatype
texts
mediatype
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collection:
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nasa_techdocs
collection
nasa_techdocs
collection
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title:
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Wind Tunnel Testing of Various Disk-Gap-Band Parachutes
title
Wind Tunnel Testing of Various Disk-Gap-Band Parachutes
title
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description:
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Two Disk-Gap-Band model parachute designs were tested in the NASA Langley Transonic Dynamics Tunnel. The purposes of these tests were to determine the drag and static stability coefficients of these two model parachutes at various subsonic Mach numbers in support of the Mars Exploration Rover mission. The two model parachute designs were designated 1.6 Viking and MPF. These model parachute designs were chosen to investigate the tradeoff between drag and static stability. Each of the parachute designs was tested with models fabricated from MIL-C-7020 Type III or F-111 fabric. The reason for testing model parachutes fabricated with different fabrics was to evaluate the effect of fabric permeability on the drag and static stability coefficients. Several improvements over the Viking-era wind tunnel tests were implemented in the testing procedures and data analyses. Among these improvements were corrections for test fixture drag interference and blockage effects, and use of an improved test fixture for measuring static stability coefficients. The 1.6 Viking model parachutes had drag coefficients from 0.440 to 0.539, while the MPF model parachutes had drag coefficients from 0.363 to 0.428. The 1.6 Viking model parachutes had drag coefficients 18 to 22 percent higher than the MPF model parachute for equivalent fabric materials and test conditions. Model parachutes of the same design tested at the same conditions had drag coefficients approximately 11 to 15 percent higher when manufactured from F-111 fabric as compared to those fabricated from MIL-C-7020 Type III fabric. The lower fabric permeability of the F-111 fabric was the source of this difference. The MPF model parachutes had smaller absolute statically stable trim angles of attack as compared to the 1.6 Viking model parachutes for equivalent fabric materials and test conditions. This was attributed to the MPF model parachutes larger band height to nominal diameter ratio. For both designs, model parachutes fabricated from F-111 fabric had significantly greater statically stable absolute trim angles of attack at equivalent test conditions as compared to those fabricated from MILC-7020 Type III fabric. This reduction in static stability exhibited by model parachutes fabricated from F-111 fabric was attributed to the lower permeability of the F-111 fabric. The drag and static stability coefficient results were interpolated to obtain their values at Mars flight conditions using total porosity as the interpolating parameter.
description
Two Disk-Gap-Band model parachute designs were tested in the NASA Langley Transonic Dynamics Tunnel. The purposes of these tests were to determine the drag and static stability coefficients of these two model parachutes at various subsonic Mach numbers in support of the Mars Exploration Rover mission. The two model parachute designs were designated 1.6 Viking and MPF. These model parachute designs were chosen to investigate the tradeoff between drag and static stability. Each of the parachute designs was tested with models fabricated from MIL-C-7020 Type III or F-111 fabric. The reason for testing model parachutes fabricated with different fabrics was to evaluate the effect of fabric permeability on the drag and static stability coefficients. Several improvements over the Viking-era wind tunnel tests were implemented in the testing procedures and data analyses. Among these improvements were corrections for test fixture drag interference and blockage effects, and use of an improved test fixture for measuring static stability coefficients. The 1.6 Viking model parachutes had drag coefficients from 0.440 to 0.539, while the MPF model parachutes had drag coefficients from 0.363 to 0.428. The 1.6 Viking model parachutes had drag coefficients 18 to 22 percent higher than the MPF model parachute for equivalent fabric materials and test conditions. Model parachutes of the same design tested at the same conditions had drag coefficients approximately 11 to 15 percent higher when manufactured from F-111 fabric as compared to those fabricated from MIL-C-7020 Type III fabric. The lower fabric permeability of the F-111 fabric was the source of this difference. The MPF model parachutes had smaller absolute statically stable trim angles of attack as compared to the 1.6 Viking model parachutes for equivalent fabric materials and test conditions. This was attributed to the MPF model parachutes larger band height to nominal diameter ratio. For both designs, model parachutes fabricated from F-111 fabric had significantly greater statically stable absolute trim angles of attack at equivalent test conditions as compared to those fabricated from MILC-7020 Type III fabric. This reduction in static stability exhibited by model parachutes fabricated from F-111 fabric was attributed to the lower permeability of the F-111 fabric. The drag and static stability coefficient results were interpolated to obtain their values at Mars flight conditions using total porosity as the interpolating parameter.
description
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subject:
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NASA PROGRAMS
subject
NASA PROGRAMS
subject
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subject:
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RESEARCH AND DEVELOPMENT
subject
RESEARCH AND DEVELOPMENT
subject
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subject:
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SOFTWARE ENGINEERING
subject
SOFTWARE ENGINEERING
subject
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subject:
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ARTIFICIAL INTELLIGENCE
subject
ARTIFICIAL INTELLIGENCE
subject
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subject:
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HUMAN-COMPUTER INTERFACE
subject
HUMAN-COMPUTER INTERFACE
subject
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subject:
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COMPUTER NETWORKS
subject
COMPUTER NETWORKS
subject
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subject:
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SUPERCOMPUTERS
subject
SUPERCOMPUTERS
subject
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subject:
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SYSTEMS ENGINEERING
subject
SYSTEMS ENGINEERING
subject
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subject:
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MACHINE LEARNING
subject
MACHINE LEARNING
subject
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subject:
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RESEARCH FACILITIES
subject
RESEARCH FACILITIES
subject
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subject:
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INFORMATION SYSTEMS
subject
INFORMATION SYSTEMS
subject
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identifier:
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nasa_techdoc_2003006 4894
identifier
nasa_techdoc_2003006 4894
identifier
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licenseurl:
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uploader:
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gwilliam@archive.org
uploader
gwilliam@archive.org
uploader
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addeddate:
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2011-06-01 05:59:45
addeddate
2011-06-01 05:59:45
addeddate
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publicdate:
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2011-06-01 05:59:45
publicdate
2011-06-01 05:59:45
publicdate
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creator:
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Cruz, Juan R.
creator
Cruz, Juan R.
creator
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creator:
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Mineck, Raymond E.
creator
Mineck, Raymond E.
creator
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creator:
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Keller, Donald F.
creator
Keller, Donald F.
creator
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creator:
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Bobskill, Maria V
creator
Bobskill, Maria V
creator
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ImageUID:
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file:/home/lunaadmin /Source_download/201 106/1/nasa_techdoc_2 0030064894/200300648 94.pdf
ImageUID
file:/home/lunaadmin /Source_download/201 106/1/nasa_techdoc_2 0030064894/200300648 94.pdf
ImageUID
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date:
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2003
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rights:
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Public Domain
rights
Public Domain
rights
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ppi:
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300
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year:
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2003
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language:
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eng
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document-source:
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CASI
document_source
CASI
document-source
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documentid:
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20030064894
documentid
20030064894
documentid
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nasa-center:
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Jet Propulsion Laboratory; Langley Research Center
nasa_center
Jet Propulsion Laboratory; Langley Research Center
nasa-center
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online-source:
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http://wayback.archi ve-it.org/1792/20100 213115721/http://hdl .handle.net/2060/200 30064894
online_source
http://wayback.archi ve-it.org/1792/20100 213115721/http://hdl .handle.net/2060/200 30064894
online-source
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original-nasa-rights:
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Unclassified; No Copyright; Unlimited; Publicly available; Annual Report
original_nasa_rights
Unclassified; No Copyright; Unlimited; Publicly available; Annual Report
original-nasa-rights
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updated-added-to-ntrs:
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2008-06-02
updated_added_to_ntr s
2008-06-02
updated-added-to-ntr s
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contributor:
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NASA
contributor
NASA
contributor
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identifier-access:
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identifier_access
identifier-access
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identifier-ark:
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ark:/13960/t6640mv3s
identifier_ark
ark:/13960/t6640mv3s
identifier-ark
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ocr:
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ABBYY FineReader 8.0
ocr
ABBYY FineReader 8.0
ocr
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repub_state:
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4
repub_state
4
repub_state
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