Experimental Surface Pressure Data Obtained On 65 O Delta Wing Across Reynolds Number And Mach Number Ranges
Download Experimental Surface Pressure Data Obtained On 65 O Delta Wing Across Reynolds Number And Mach Number Ranges full books in PDF, epub, and Kindle. Read online free Experimental Surface Pressure Data Obtained On 65 O Delta Wing Across Reynolds Number And Mach Number Ranges ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
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 |
| Total Pages | : 598 |
| Release | : 2018-07-24 |
| Genre | : |
| ISBN | : 9781723576010 |
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 2; Small-Radius Leading Edge
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 518 |
| Release | : 2018-07-24 |
| Genre | : |
| ISBN | : 9781723576270 |
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. 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 |
| Total Pages | : 286 |
| Release | : 2018-07-24 |
| Genre | : |
| ISBN | : 9781723576164 |
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...
New Results in Numerical and Experimental Fluid Mechanics VIII
| Author | : Andreas Dillmann |
| Publisher | : Springer Science & Business Media |
| Total Pages | : 747 |
| Release | : 2012-12-27 |
| Genre | : Technology & Engineering |
| ISBN | : 364235680X |
This 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.
