منابع مشابه
Low-Speed Wind-Tunnel Tests on some Slender Airbus Configurations
An experimentalinvestigation has been made of the subsonic lift, drag and longitudinal stability characteristics of models representing some alternative slender airbus configurations. For the same wing planform of aspect ratio 1.4 the lift, drag and pitching moment have been measured for two wings of maximum thickness/chord ratio 4 and 9 per cent respectively, both without and with various body...
متن کاملSmall Propeller and Rotor Testing Capabilities of the NASA Langley Low Speed Aeroacoustic Wind Tunnel
The Low Speed Aeroacoustic Wind Tunnel (LSAWT) at NASA Langley Research Center has recently undergone a configuration change. This change incorporates an inlet nozzle extension meant to serve the dual purposes of achieving lower freestream velocities as well as a larger core flow region. The LSAWT, part of the NASA Langley Jet Noise Laboratory, had historically been utilized to simulate realist...
متن کاملLow-cost wind tunnel for micro-arthropods
The aerial transport of tiny arthropods including wing-less species has been well documented. The initiation of aerial dispersal in most instances is not a passive phenomenon, but involves identifiable behaviors in response to specific stimuli. Here we describe a construction of wind tunnel suitable for close-up observation of micro-arthropods behavior under various conditions. The tunnel was m...
متن کاملAc 2007-1191: Design, Fabrication and Testing of a Low-speed Wind Tunnel Laboratory
Engineering Technology programs focus on delivering a hands-on engineering education. The students get introduced to the theoretical development of engineering concepts first, then they apply the concepts to solve practical problems and test the concepts in carefully designed experiments carried out in appropriate facilities. One of the key areas of instruction associated with a mechanical engi...
متن کاملLow-Speed Wind-Tunnel Measurements 1 of Damping in Yaw (nv) on an A.R.9 Jet-Flap Complete -Model bY
Measurements have been made cf the yaw-dam@g derivative, n A.R.9 jet-flap ccm$ete model, SI' a*; using the free-oscillation technique. experimental apparatus and procedure are fullydescribtd, with the exception of the special air-bearing support system, which has been the subject of a previcus Repcrt. Results are given cf damping i,leasurements at wing incidence9 of Oc, qOc and 20' with jet-fla...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Journal of the Visualization Society of Japan
سال: 1995
ISSN: 1884-037X,0916-4731
DOI: 10.3154/jvs.15.supplement1_281