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Pivotable strakes for high angle of attack controlA series of pivotable strakes have been tested in combination with a 44-deg swept wing to determine their ability to provide pitch control at high angles of attack. The tests were carried out in the Langley 7 X 10-Foot High-Speed tunnel at nominal Mach numbers of 0.3 to 0.4. A total of five strakes with various aspects ratios and shapes were tested at negative deflection angles of 5, 10, 15, and 20 deg through an angle of attack range up to approximately 50 deg. In addition, a cranked delta wing with 70-deg sweep was tested with two different pivotable apex flaps. This paper shows lift, drag and moment data for the complete configurations as well as for the separate contributions of the strakes and fuselage nose which are mounted on a second balance. Generally, strake deflection was found to have a significant effect on moment while lift/drag changed very little.
Document ID
19860053591
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bobbitt, P. J.
(NASA Langley Research Center Hampton, VA, United States)
Foughner, J. T., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1985
Subject Category
Aircraft Stability And Control
Report/Patent Number
SAE PAPER 851821
Accession Number
86A38329
Distribution Limits
Public
Copyright
Other

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