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Lateral control at high angles of attack using pneumatic blowing through a chined forebodyDirectional control through the use of pneumatic blowing was investigated on a generic subscale model with a chined forebody with blowing through a chine slot in a direction normal to the forebody surface. Comparisons are made with a vertical tail on and off, and with control through rudder deflection. Force and moment data were obtained for various blowing coefficients over a 0-75 deg alpha range, and flow visualization was also conducted in order to see qualitative effects on the flowfield. Blowing through a chined forebody generates yaw moments at large alpha where control surfaces lose their effectiveness; these moments are much larger than obtained by jet thrust alone, since the forebody flowfield is modified through the interaction of the jet with the chine vortices. Directional control increased with angle of attack for a given blowing coefficient until a maximum was reached. Further increases in angle of attack results in a rapid loss of effectiveness. For angles of attack above 60 deg, yaw moments are generated by simple jet thrust effect. The effectiveness of the pneumatic system depended on tail configuration.
Document ID
19930064312
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Arena, A. S., Jr.
(Oklahoma State Univ. Stillwater, United States)
Nelson, R. C.
(Notre Dame Univ. IN, United States)
Schiff, L. B.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Atmospheric Flight Mechanics Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers (A93-48301 20-08)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 93-3624
Accession Number
93A48309
Funding Number(s)
CONTRACT_GRANT: NCA2-621
Distribution Limits
Public
Copyright
Other

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