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Wind tunnel force and pressure tests of a 21% thick general aviation airfoil with 20% aileron, 25% slotted flap and 10% slot-lip spoilerForce and surface pressure distributions were measured for the 21% LS(1)-0421 modified airfoil fitted with 20% aileron, 25% slotted flap and 10% slot lip spoiler. All tests were conducted at a Reynolds number of 2.2 x 10 to the 6th power and a Mach number of 0.13. The lift, drag, pitching moments, control surface normal force and hinge moments, and surface pressure distributions are included in the results. Incremental performance of flap and aileron are discussed and compared to the GA(W)-2 airfoil. Spoiler control which shows a slight reversal tendency at high alpha, is examined.
Document ID
19800003803
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wentz, W. H., Jr. (Wichita State Univ. Wichita, KS, United States)
Fiscko, K. A. (Wichita State Univ. Wichita, KS, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1979
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
WSU-AR-77-6
NASA-CR-3081
Accession Number
80N12053
Funding Number(s)
PROJECT: RTOP 505-06-33-10
CONTRACT_GRANT: NSG-1165
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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