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Computations of two-dimensional airfoil-vortex interactionsA procedure for calculating the interaction of a vortex with a two dimensional airfoil in a uniform free stream is presented along with results for several test cases. A Lamb like anaytical vortex having a finite core and convect in a uniform free stream interacts with the flowfield of NACA 0012 or NACA 64A006 airfoil in transonic and subsonic flow. Euler and thin layer Navier-Stokes solutions are computed and the results are compared with the results from transonic small disturbance code and available experimental results. For interactions within the limits of transonic small disturbance assumptions, the three methods gave qualitatively similar results of a two bladed helicopter rotor and suggest that the time lag effects of the free stream velocity approaching the blade may be important and should be considered in the analysis. In general, the results show a tremendous influence of the interacting vortex on the flowfield around the airfoil. This is particularly true when the vortex is stationary. For a convecting vortex, the most dramatic changes in the flowfield seem to occur when the vortex is within one chord of the airfoil.
Document ID
19850015398
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Srinivasan, G. R. (Flow Simulations, Inc. Sunnyville, CA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1985
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3885
NAS 1.26:3885
FSI-84-01
Accession Number
85N23709
Funding Number(s)
CONTRACT_GRANT: NAS2-11331
PROJECT: RTOP 505-31-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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