3 edition of On-line analysis capabilities developed to support the AFW wind-tunnel tests found in the catalog.
On-line analysis capabilities developed to support the AFW wind-tunnel tests
Carol D. Wieseman
1992 by National Aeronautics and Space Administration, Langley Research Center, For sale by the National Technical Information Service in Hampton, Va, [Springfield, Va .
Written in English
|Other titles||On line analysis capabilities developed ....|
|Statement||Carol D. Wieseman, Sherwood T. Hoadley, and Sandra M. McGraw.|
|Series||NASA technical memorandum -- 107651.|
|Contributions||Hoadley, Sherwood Tiffany., McGraw, Sandra M., Langley Research Center.|
|The Physical Object|
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On-line analysis capabilities developed to support the AFW wind-tunnel tests (SuDoc NAS ) [Carol D. Wieseman] on *FREE* shipping on qualifying : Carol D. Wieseman. Get this from a library. On-line analysis capabilities developed to support the AFW wind-tunnel tests.
[Carol D Wieseman; Sherwood T Hoadley; Sandra M McGraw; Langley Research Center.]. Buy On-line analysis capabilities developed to support the AFW wind-tunnel tests (SuDoc NAS ) by Carol D.
Wieseman (ISBN:) from Amazon's Book Store. Everyday low prices and free delivery on eligible : Carol D. Wieseman. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA This paper describes the development of transfer function models for the trailing edge and upper- and lower-spoiler actuators of the Benchmark Active Control Technology (BACT) wind Author: Martin Waszak.
On-line analysis capabilities developed to support the active flexible wing wind-tunnel tests (AFW) wind-tunnel tests. These tools were developed to verify control law execution, to satisfy. capabilities, primarily because of its large size, heavy gas test medium and transonic speed capabilities.
Fig. 1- Aerial photograph of the TDT. The TDT had a significant success within months of coming on-line. In late and early the Lockheed Electra aircraft experienced two catastrophic crashes. Evidence from these crashes pointed in the. Low-speed aerodynamic tests were carried out on a A aircraft model, designated as model DB1.
The tests were performed in the closed 8 m x 6 m test section of the DNW-LLF low-speed wind tunnel. AIRBUS has adapted a scale model of a A such as to represent the BLADE flying Size: KB.
On-line analysis capabilities developed to support the AFW wind-tunnel tests. NASA Technical Reports Server (NTRS) Wieseman, Carol D.; Hoadley, Sherwood T.; Mcgraw, Sandra M. Gameday Meets the Knuckleball, an article by Dan Fox published in Baseball Prospectus in June The article analyzes the movement of Tim Wakefield's pitches.
It is the first article of which I am aware to use PITCHf/x data to study the knuckleball and the first to examine, both qualitatively and quantitaviely, the movement of the pitch. Several specialized piercing methods have been developed to alleviate some of these limitations, with varying efficiencies and effectiveness.
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Animation depicts the nose of the XSM Series A missile being separated and enters the earths atmosphere. The hydrogen oxygen wind tunnel being used to test the missile nose under specified temperature and wind velocity conditions.
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A variety of on-line analysis tools were developed to support two active flexible wing (AFW) wind-tunnel tests.
These tools were developed to verify control. “Covered Government support contractor” is defined in (a)(6) as “a contractor under a contract, the primary purpose of which is to furnish independent and impartial advice or technical assistance directly to the Government in support of the Government’s management and oversight of a program or effort (rather than to directly.
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Sara Burgerhartstraat 25 P.O. BoxAE Amsterdam, The Netherlands. Tests of new wing Neal T. Frink of Langley and his associates conducted extensive pioneering wind-tunnel tests designs in indicated a supersonic performance improvement of about 30 percent compared with to evaluate the eﬀects of wing-sweep angle and other geometric characteristics on vortex-ﬂap the basic F At subsonic speeds, the 5/5(2).
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