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CFD Study of NACA 0018 Airfoil with Flow ControlThe abilities of two different Reynolds-Averaged Navier-Stokes codes to predict the effects of an active flow control device are evaluated. The flow control device consists of a blowing slot located on the upper surface of an NACA 0018 airfoil, near the leading edge. A second blowing slot present on the airfoil near mid-chord is not evaluated here. Experimental results from a wind tunnel test show that a slot blowing with high momentum coefficient will increase the lift of the airfoil (compared to no blowing) and delay flow separation. A slot with low momentum coefficient will decrease the lift and induce separation even at low angles of attack. Two codes, CFL3D and FUN3D, are used in two-dimensional computations along with several different turbulence models. Two of these produced reasonable results for this flow, when run fully turbulent. A more advanced transition model failed to predict reasonable results, but warrants further study using different inputs. Including inviscid upper and lower tunnel walls in the simulations was found to be important in obtaining pressure distributions and lift coefficients that best matched experimental data. A limited number of three-dimensional computations were also performed.
Document ID
20170004500
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Eggert, Christopher A. (Purdue Univ. West Lafayette, IN, United States)
Rumsey, Christopher L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
May 9, 2017
Publication Date
April 1, 2017
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NASA/TM-2017-219602
NF1676L-26639
L-20799
Funding Number(s)
WBS: WBS 109492.02.07.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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