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Investigation of aerodynamic characteristics of subsonic wingsAn analytical strake design procedure is investigated. A numerical solution to the governing strake design equation is used to generate a series of strakes which are tested in a water tunnel to study their vortex breakdown characteristics. The strakes are scaled for use on a half-scale model of the NASA-LaRC general research fuselage with a 44 degrees trapezoidal wing. An analytical solution to the governing design equation is obtained. The strake design procedure relates the potential-flow leading-edge suction and pressure distributions to vortex stability. Several suction distributions are studied and those which are more triangular and peak near the tip generate strakes that reach higher angles of attack before vortex breakdown occurs at the wing trailing edge. For the same suction distribution, a conical rather than three dimensional pressure specification results in a better strake shape as judged from its vortex breakdown characteristics.
Document ID
19790015750
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Dejarnette, F. R. (North Carolina State Univ. Raleigh, NC, United States)
Frink, N. T. (North Carolina State Univ. Raleigh, NC, United States)
Date Acquired
September 4, 2013
Publication Date
June 11, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-158661
Accession Number
79N23921
Funding Number(s)
CONTRACT_GRANT: NSG-1437
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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