Aerodynamic Performance of an Active Flow Control Configuration Using Unstructured-Grid RANS

Joslin, Ronald D.; Viken, Sally A.

This research is focused on assessing the value of the Reynolds-Averaged Navier-Stokes (RANS) methodology for active flow control applications. An experimental flow control database exists for a TAU0015 airfoil, which is a modification of a NACA0015 airfoil. The airfoil has discontinuities at the leading edge due to the implementation of a fluidic actuator and aft of mid chord on the upper surface. This paper documents two- and three-dimensional computational results for the baseline wing configuration (no control) with tile experimental results. The two-dimensional results suggest that the mid-chord discontinuity does not effect the aerodynamics of the wing and can be ignored for more efficient computations. The leading-edge discontinuity significantly affects tile lift and drag; hence, the integrity of the leading-edge notch discontinuity must be maintained in the computations to achieve a good match with the experimental data. The three-dimensional integrated performance results are in good agreement with the experiments inspite of some convergence and grid resolution issues.

Document ID

20010006166

Acquisition Source

Langley Research Center

Document Type

Preprint (Draft being sent to journal)

Authors

Date Acquired

September 7, 2013

Publication Date

January 1, 2001

Subject Category

Report/Patent Number

Meeting Information

Meeting: Aerospace Sciences

Location: Reno, NV

Country: United States

Start Date: January 8, 2001

End Date: January 11, 2001

Sponsors: American Inst. of Aeronautics and Astronautics

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Public

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