Author : Julio Chu
Publisher :
Page : 34 pages
File Size : 16,47 MB
Release : 1996
Category : Angle of attack
ISBN :
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 598 pages
File Size : 21,92 MB
Release : 2018-07-24
Category :
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...
Author :
Publisher :
Page : 34 pages
File Size : 29,86 MB
Release : 1996
Category :
ISBN :
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 518 pages
File Size : 28,17 MB
Release : 2018-07-24
Category :
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...
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 286 pages
File Size : 17,53 MB
Release : 2018-07-24
Category :
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...
Author : Julio Chu
Publisher :
Page : pages
File Size : 11,26 MB
Release : 1996
Category : Angle of attack
ISBN :
Author :
Publisher :
Page : 180 pages
File Size : 29,37 MB
Release : 1997
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 650 pages
File Size : 25,41 MB
Release : 1996
Category : Science
ISBN :
Author : Andreas Dillmann
Publisher : Springer Science & Business Media
Page : 747 pages
File Size : 29,99 MB
Release : 2012-12-27
Category : 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.
Author : American Institute of Aeronautics and Astronautics
Publisher :
Page : 1252 pages
File Size : 28,86 MB
Release : 2003
Category : Aeronautics
ISBN :
