Experimental Surface Pressure Data Obtained on 65 Deg Delta Wing Across Reynolds Number and Mach Number Ranges. Volume 2; Small-Radius Leading Edge

Experimental Surface Pressure Data Obtained on 65 Deg Delta Wing Across Reynolds Number and Mach Number Ranges. Volume 2; Small-Radius Leading Edge PDF

Author: National Aeronautics and Space Administration (NASA)

Publisher: Createspace Independent Publishing Platform

Published: 2018-07-24

Total Pages: 518

ISBN-13: 9781723576270

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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

Experimental Surface Pressure Data Obtained on 65 Deg Delta Wing Across Reynolds Number and Mach Number Ranges. Vol. 4 PDF

Author: National Aeronautics and Space Administration (NASA)

Publisher: Createspace Independent Publishing Platform

Published: 2018-07-24

Total Pages: 598

ISBN-13: 9781723576010

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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 Deg Delta Wing Across Reynolds Number and Mach Number Ranges. Volume 1; Sharp Leading Edge; Conducted in the Langley National Transonic Facility (Ntf)

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) PDF

Author: National Aeronautics and Space Administration (NASA)

Publisher: Createspace Independent Publishing Platform

Published: 2018-07-24

Total Pages: 286

ISBN-13: 9781723576164

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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...

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