Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges Volume 1 Sharp Leading Edge Conducted In The Langley National Transonic Facility Ntf
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Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges
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Author :
language : en
Publisher:
Release Date : 1996
Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges Volume 1 Sharp Leading Edge Conducted In The Langley National Transonic Facility Ntf
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-24
Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges Volume 1 Sharp Leading Edge Conducted In The Langley National Transonic Facility Ntf written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-24 with categories.
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was conducted in the Langley National Transonic Facility (NTF). The objective was to investigate the effects of Reynolds and Mach numbers on slender-wing leading-edge vortex flows with four values of wing leading-edge bluntness. Experimentally obtained pressure data are presented without analysis in tabulated and graphical formats across a Reynolds number range of 6 x 10(exp 6) to 36 x 10(exp 6) at a Mach number of 0.85 and across a Mach number range of 0.4 to 0.9 at a Reynolds number of 6 x 10(exp 6). Normal-force and pitching-moment coefficient plots for these Reynolds number and Mach number ranges are also presented. Chu, Julio and Luckring, James M. Langley Research Center NASA-TM-4645-Vol-1, L-17411A, NAS 1.15:4645-Vol-1 RTOP 505-59-54-01...
Scientific And Technical Aerospace Reports
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Author :
language : en
Publisher:
Release Date : 1993
Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with Aeronautics categories.
Government Reports Announcements Index
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Author :
language : en
Publisher:
Release Date : 1996
Government Reports Announcements Index written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with Science categories.
Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges Volume 2 Small Radius Leading Edge
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-24
Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges Volume 2 Small Radius Leading Edge written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-24 with categories.
An experimental wind tunnel test of a 65 deg. delta wing model with interchangeable leading edges was conducted in the Langley National Transonic Facility (NTF). The objective was to investigate the effects of Reynolds and Mach numbers on slender-wing leading-edge vortex flows with four values of wing leading-edge bluntness. Experimentally obtained pressure data are presented without analysis in tabulated and graphical formats across a Reynolds number range of 6 x 10(exp 6) to 84 x 10(exp 6) at a Mach number of 0.85 and across a Mach number range of 0.4 to 0.9 at Reynolds numbers of 6 x 10(exp 6) and 60 x 10(exp 6). Normal-force and pitching-moment coefficient plots for these Reynolds number and Mach number ranges are also presented. Chu, Julio and Luckring, James M. Langley Research Center NASA-TM-4645-Vol-2, L-17411B-Vol-2, NAS 1.15:4645-Vol-2 RTOP 505-59-54-01...
Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges Vol 4
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-24
Experimental Surface Pressure Data Obtained On 65 Deg Delta Wing Across Reynolds Number And Mach Number Ranges Vol 4 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-24 with categories.
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was conducted in the Langley National Transonic Facility (NTF). The objective was to investigate the effects of Reynolds and Mach numbers on slender-wing leading-edge vortex flows with four values of wing leading-edge bluntness. Experimentally obtained pressure data are presented without analysis in tabulated and graphical formats across a Reynolds number range of 6 x 10(exp 6) to 120 x 10(exp 6) at a Mach number of 0.85 and across a Mach number range of 0.4 to 0.9 at Reynolds numbers of 6 x 10(exp 6) and 60 x 10(exp 6). Normal-force and pitching-moment coefficient plots for these Reynolds number and Mach number ranges are also presented. Chu, Julio and Luckring, James M. Langley Research Center NASA-TM-4645-Vol-4, L-17411D-Vol-4, NAS 1.15:4645-Vol-4 RTOP 505-59-54-01...
Experimental Surface Pressure Data Obtained On 65 Delta Wing Across Reynolds Number And Mach Number Ranges
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Author : Julio Chu
language : en
Publisher:
Release Date : 1996
Experimental Surface Pressure Data Obtained On 65 Delta Wing Across Reynolds Number And Mach Number Ranges written by Julio Chu and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with Angle of attack categories.
Experimental Surface Pressure Data Obtained On 65 Delta Wing Across Reynolds Number And Mach Number Ranges
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Author : Julio Chu
language : en
Publisher:
Release Date : 1996
Experimental Surface Pressure Data Obtained On 65 Delta Wing Across Reynolds Number And Mach Number Ranges written by Julio Chu and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with Angle of attack categories.
Experimental Surface Pressure Data Obtained On 65 O Delta Wing Across Reynolds Number And Mach Number Ranges
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Author : Julio Chu
language : en
Publisher:
Release Date : 1996
Experimental Surface Pressure Data Obtained On 65 O Delta Wing Across Reynolds Number And Mach Number Ranges written by Julio Chu and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
Surface Pressure And Flow Visualization Data At Mach Number Of 1 60 For Three 65 Deg Delta Wings Varying In Leading Edge Radius And Camber
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-08-04
Surface Pressure And Flow Visualization Data At Mach Number Of 1 60 For Three 65 Deg Delta Wings Varying In Leading Edge Radius And Camber written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-08-04 with categories.
An experimental investigation of the effect of leading-edge radius, camber, Reynolds number, and boundary-layer state on the incipient separation of a delta wing at supersonic speeds was conducted at the Langley Unitary Plan Wind Tunnel at Mach number of 1.60 over a free-stream Reynolds number range of 1 x 106 to 5 x 106 ft-1. The three delta wing models examined had a 65 deg swept leading edge and varied in cross-sectional shape: a sharp wedge, a 20:1 ellipse, and a 20:1 ellipse with a -9.750 circular camber imposed across the span. The wings were tested with and without transition grit applied. Surface-pressure coefficient data and flow-visualization data indicated that by rounding the wing leading edge or cambering the wing in the spanwise direction, the onset of leading-edge separation on a delta wing can be raised to a higher angle of attack than that observed on a sharp-edged delta wing. The data also showed that the onset of leading-edge separation can be raised to a higher angle of attack by forcing boundary-layer transition to occur closer to the wing leading edge by the application of grit or the increase in free-stream Reynolds number. McMillin, S. Naomi and Bryd, James E. and Parmar, Devendra S. and Bezos-OConnor, Gaudy M. and Forrest, Dana K. and Bowen, Susan Langley Research Center NASA-TM-4673, NAS 1.15:4673, L-17443 RTOP 505-59-53-05...