3 edition of NASA Lewis 8- by 6-foot supersonic wind tunnel user manual found in the catalog.
NASA Lewis 8- by 6-foot supersonic wind tunnel user manual
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va
Written in English
|Statement||Ronald H. Soeder.|
|Series||NASA technical memorandum -- 105771|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
In collaboration with NASA and Howard Hughes, the Department of Defense was spending billions to develop a Supersonic Tunneling Underground Device, or STUD. It was supposed to tunnel through the earth’s core at great speed and deliver a specially designed atomic warhead ‘‘right up the Red’s missile silos,’’ as one of the Pentagon. The user interface is visual as well as multi-touch similar to the apple iphone. It additionally has a streamlined design but the apple iphone has extra attractive functions. Unlike the apple iphone, the Touch has no microphone, Bluetooth compatibility, GPS receiver, and also electronic camera.
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Get this from a library. NASA Lewis 8- by 6-foot supersonic wind tunnel user manual. [Ronald H Soeder; United States. National Aeronautics and Space Administration.].
This compressor produ miles per hour air speeds for research in the 8-By 6-Foot 6 Supersonic Wind Tunnel (). Lewis Inspection At the September Inspection, the NACA unveiled Lewis’ recently completed 8-by 6-Foot Supersonic Wind Tunnel and a new style of presenting the technical information in a more understandable manner.
Figure 3.—Dual-stream inlet in the NASA Glenn 8- by 6-Foot Supersonic Wind Tunnel. Figure 4.—Dual-stream inlet model and support hardware. The inlet models were mounted on a hydraulic strut that could be rotated to vary the angle of attack from –2 to +5°.
Yaw angles could not be varied. The core stream of each model expanded through a. foot Supersonic Wind Tunnel, ” AIAA Paper 98–, 4 Wang, X., and Yang, H., “Hierarchical Mu ltiple Models Adaptive Feedforward Decoupling Controller Applied to Wind. A test section calibration of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel was conducted to provide calibration and flow quality data over the low-speed range of the facility.
Computational tools used to calculate the detailed flow and acoustic fields are described along with wind tunnel tests to obtain data for code verification. Results from two kinds of experiments are reviewed: (1) performance and near field noise at cruise conditions as measured in the NASA Lewis 8- by.
NASA Images Solar System Collection Ames Research Center. Brooklyn Museum. Full text of "NASA Technical Reports Server (NTRS) Bibliography of Lewis Research Center technical publications announced in ". NASA Lewis wind tunnel model systems criteria [microform] / Ronald H. Soeder and Henry C.
Haller; Flow quality studies of the NASA Lewis Research Center 8- by 6-foot supersonic/9- by foot low speed w User manual for NASA Lewis by Foot Supersonic Wind Tunnel [microform] /. Library of Congress Cataloging-in-Publication Data (Revised for vol. 8) NASA historical data book.
(NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C. Bruno. Vol. 8 in series: The NASA historical data book series.
Includes bibliographical references and indexes. NASA Glenn Research Center Annual Report. Comments. Content. NASA/TM— RESEARCH & TECHNOLOGY Lewis Field, is situated on acres adjacent to NASA Glenn’s 8- by 6-Foot Supersonic Wind Tunnel/9- by Foot Low-Speed Wind Tunnel Control.
Lewis Research Center: Comparison between design and installed acoustic characteristics of NASA Lewis 9- by Foot Low-Speed Wind Tunnel acoustic treatment / (Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va.
NASA Images Solar System Collection Ames Research Center. Brooklyn Museum. Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )". A transonic wind-tunnel investigation of the longitudinal force and moment characteristics of two delta wings and one clipped-tip delta wing of 4 percent thickness on a slender body /, by William E.
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