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1997•Journal of AircraftRequires access

Unsteady Pressure Measurements for Parallel Vortex-Airfoil Interaction at Low Speed

Jerry M. Chen, Dar-Ming Chang

Open publisher page 11 citations

Abstract

Two-dimensional vortex-airfoil interaction at airfoil chord Reynolds number 6 x 10 4 is studied experimentally by immersing an instrumented NACA 0012 airfoil downstream of a vortex generator airfoil that pitches in a tailored nonsinusoidal form. A clockwise rotating vortex is generated to approach the target airfoil from left to right. When the vortex interacts with a nonlifting airfoil, it creates rather sharp and local variations of surface pressure in the vicinity of the leading edge.

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What this paper is about

Two-dimensional vortex-airfoil interaction at airfoil chord Reynolds number 6 x 10 4 is studied experimentally by immersing an instrumented NACA 0012 airfoil downstream of a vortex generator airfoil that pitches in a tailored nonsinusoidal form. A clockwise rotating vortex is generated to approach the target airfoil from left to right. When the vortex interacts with a nonlifting airfoil, it creates rather sharp and local variations of surface pressure in the vicinity of the leading edge.

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OpenAlex reports 11 citations for this work. Citation counts describe recorded attention and do not establish research quality.

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Available abstract

Two-dimensional vortex-airfoil interaction at airfoil chord Reynolds number 6 x 10 4 is studied experimentally by immersing an instrumented NACA 0012 airfoil downstream of a vortex generator airfoil that pitches in a tailored nonsinusoidal form. A clockwise rotating vortex is generated to approach the target airfoil from left to right. When the vortex interacts with a nonlifting airfoil, it creates rather sharp and local variations of surface pressure in the vicinity of the leading edge.

Key concepts: Airfoil, Vortex, Mechanics, Aerospace engineering, Physics, Vortex shedding, Acoustics, Reynolds number

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