Scientific and Technical Aerospace Reports Volume 39 April 6, 2001

The Models for Aeroelastic Validation Research Involving Computation semi-span wind-tunnel model (MAVRIC-I), a business
jet wing-fuselage flutter model, was tested in NASA Langley’s Transonic Dynamics Tunnel with the goal of obtaining experimental
data suitable for Computational Aeroelasticity code validation at transonic separation onset conditions. This research
model is notable for its inexpensive construction and instrumentation installation procedures. Unsteady pressures and wing
responses were obtained for three wingtip configurations clean, tipstore, and winglet. Traditional flutter boundaries were measured
over the range of M = 0.6 to 0.9 and maps of Limit Cycle Oscillation (LCO) behavior were made in the range of M = 0.85
to 0.95. Effects of dynamic pressure and angle-of-attack were measured. Testing in both R134a heavy gas and air provided unique
data on Reynolds number, transition effects, and the effect of speed of sound on LCO behavior. The data set provides excellent
code validation test cases for the important class of flow conditions involving shock-induced transonic flow separation onset at
low wing angles, including Limit Cycle Oscillation behavior.
Author
Flutter Analysis; Semispan Models; Wind Tunnel Models; Transonic Wind Tunnels; Aeroelasticity; Flutter
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RESEARCH AND SUPPORT FACILITIES (AIR)
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20010023439 NASA Langley Research Center, Hampton, VA USA
Status of the National Transonic Facility Characterization (Invited)
Bobbitt, C., Jr., NASA Langley Research Center, USA; Everhart, J., NASA Langley Research Center, USA; [2001]; 16p; In
English; 39th; Aerospace Sciences, 8-11 Jan. 2001, Reno, NV, USA; Sponsored by American Inst. of Aeronautics and Astronautics,
USA
Report No.(s): AIAA Paper 2001-0755; Copyright Waived; Avail: CASI; A03, Hardcopy; A01, Microfiche
This paper describes the current activities at the National Transonic Facility to document the test-section flow and to support
tunnel improvements. The paper is divided into sections on the tunnel calibration, flow quality measurements, data quality assurance,
and implementation of wall interference corrections.
Author
Transonic Wind Tunnels; Aerodynamic Interference; Wall Flow; Quality Control
20010023934 NASA Langley Research Center, Hampton, VA USA
Recent National Transonic Facility Test Process Improvements (Invited)
Kilgore, W. A., NASA Langley Research Center, USA; Balakrishna, S., Vigyan Research Associates, Inc., USA; Bobbitt, C. W.,
Jr., NASA Langley Research Center, USA; Adcock, J. B., Vigyan Research Associates, Inc., USA; [2001]; 12p; In English; 39th;
Aerospace Sciences, 8-11 Jan. 2001, Reno, NV, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA
Report No.(s): AIAA Paper 2001-0756; Copyright Waived; Avail: CASI; A03, Hardcopy; A01, Microfiche
This paper describes the results of two recent process improvements; drag feed-forward Mach number control and simultaneous
force/moment and pressure testing, at the National Transonic Facility. These improvements have reduced the duration and
cost of testing. The drag feed-forward Mach number control reduces the Mach number settling time by using measured model
drag in the Mach number control algorithm. Simultaneous force/moment and pressure testing allows simultaneous collection of
force/moment and pressure data without sacrificing data quality thereby reducing the overall testing time. Both improvements
can be implemented at any wind tunnel. Additionally the NTF is working to develop and implement continuous pitch as a testing
option as an additional method to reduce costs and maintain data quality.
Author
Transonic Wind Tunnels; Wind Tunnel Tests; Mach Number; Drag; Loads (Forces); Feedforward Control; Pressure Measurement
20010024168 Federal Aviation Administration, Technical Center, Atlantic City, NJ USA
Team Processes in Airway Facilities Operations Control Centers
Ahlstrom, Vicki, Federal Aviation Administration, USA; Koros, Anton, Federal Aviation Administration, USA; Helney, Michele,
Federal Aviation Administration, USA; Jul. 2000; 32p; In English
Report No.(s): AD-A385540; ACT-500; DOT/FAA/CT-TN00/14; No Copyright; Avail: CASI; A01, Microfiche; A03, Hardcopy
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