Control Of Tip-Leakage Vortices Using Segmented Plasma Actuators: An Experimental And Numerical Study

Abstract

A combined experimental and numerical investigations were conducted to understand the effect of forcing by Dielectric-barrier-discharge (DBD) plasma actuators on the strength of the tip-leakage vortices formed in the tip-gap of a single NACA 65 airfoil. A proof-of-concept experiment was conducted, where the airfoil was mounted with variable tip gaps in the test-section of a suction-type wind tunnel. The objective was to understand the difference of three-dimensional (3D) forcing over regular two-dimensional (2D) actuation. The continuous 3D forcing was generated by using segmented DBD actuators, where the buried electrodes were designed to generate secondary vortices along the tip gap flow, and across the tip gap flow. The flow field was investigated experimentally by dynamic-pressure measurements, and by stereo-particle-image-velocimetry (SPIV). Numerical study was conducted by using RANS computations for different forcing configurations. With a tip gap of 2 mm and free stream velocity of 2.7 m/s, the strength of the tip leakage vortex was significantly attenuated for a blowing ratio of approximately 1. For the segmented forcing cases, the location of the tip-leakage vortex was altered, however no perceptible change in the strength of the vortex was observed compared to the steady forcing. Overall, the effectiveness of forcing decreased with increasing tip-gaps and free-stream velocity.

Publication Date

1-1-2018

Publication Title

2018 Flow Control Conference

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.2514/6.2018-3525

Socpus ID

85051624762 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85051624762

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