Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges
Author: Julio Chu
Publisher:
Published: 1996
Total Pages: 34
ISBN-13:
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Experimental Surface Pressure Data Obtained on 65 Deg Delta Wing Across Reynolds Number and Mach Number Ranges. Volume 2; Small-Radius Leading Edge
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-24
Total Pages: 518
ISBN-13: 9781723576270
DOWNLOAD EBOOKAn 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
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-24
Total Pages: 598
ISBN-13: 9781723576010
DOWNLOAD EBOOKAn 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
Author:
Publisher:
Published: 1996
Total Pages: 34
ISBN-13:
DOWNLOAD EBOOKExperimental 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)
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-24
Total Pages: 286
ISBN-13: 9781723576164
DOWNLOAD EBOOKAn 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...
Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges
Author: Julio Chu
Publisher:
Published: 1996
Total Pages:
ISBN-13:
DOWNLOAD EBOOKNASA Technical Memorandum
Author:
Publisher:
Published: 1997
Total Pages: 180
ISBN-13:
DOWNLOAD EBOOKGovernment Reports Announcements & Index
Author:
Publisher:
Published: 1996
Total Pages: 650
ISBN-13:
DOWNLOAD EBOOKNew Results in Numerical and Experimental Fluid Mechanics VIII
Author: Andreas Dillmann
Publisher: Springer Science & Business Media
Published: 2012-12-27
Total Pages: 747
ISBN-13: 364235680X
DOWNLOAD EBOOKThis volume contains the contributions to the 17th Symposium of STAB (German Aerospace Aerodynamics Association). STAB includes German scientists and engineers from universities, research establishments and industry doing research and project work in numerical and experimental fluid mechanics and aerodynamics, mainly for aerospace but also for other applications. Many of the contributions collected in this book present results from national and European Community sponsored projects. This volume gives a broad overview of the ongoing work in this field in Germany and spans a wide range of topics: airplane aerodynamics, multidisciplinary optimization and new configurations, hypersonic flows and aerothermodynamics, flow control (drag reduction and laminar flow control), rotorcraft aerodynamics, aeroelasticity and structural dynamics, numerical simulation, experimental simulation and test techniques, aeroacoustics as well as the new fields of biomedical flows, convective flows, aerodynamics and acoustics of high-speed trains.
AIAA Journal
Author: American Institute of Aeronautics and Astronautics
Publisher:
Published: 2003
Total Pages: 1252
ISBN-13:
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