Summary
The methodology outlined here was shown to be an effective means by which detailed unsteady surface pressure measurements may be obtained on a wing undergoing a self-induced oscillation in a wind tunnel study. Previous methods have relied on forcing the wing through a sinusoidal motion at a fixed amplitude and frequency. The advantage of the technique outlined here is that pressure measurements are obtained for the exact motion time history, including all transient motions. In fact, almost any self-induced or forced motion may be implemented by the system. The method also has the advantage of a significant reduction in the cost of pressure transducers due to the repeatability of the unsteady flowfield.
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References
Arena AS, Jr (1992) An Experimental and Computational Investigation of Slender Wings Undergoing Wing Rock, PhD Dissertation, University of Notre Dame
Arena Jr AS, Nelson RC (1992) A Discrete Vortex Model for Predicting Wing Rock of Slender Wings, AIAA Paper 92-4497
Arena Jr AS; Nelson, RC (1991) Unsteady Surface Pressure Measurements on a Slender Delta Wing Undergoing Limit Cycle Wing Rock, AIAA Paper 91-0434
Arena Jr AS; Nelson RC; Schiff LB (1990) An Experimental Study of the Nonlinear Dynamic Phenomenon Known As Wing Rock, AIAA Paper 90-2812
Arena Jr AS; Nelson RC (1989) The Effect of Asymmetric Wake Characteristics on a Slender Delta Wing Rock Motion, AIAA Paper 89-3348
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Funds for the support of this study have been allocated by the NASA-Ames Research Center, Moffett Field, California, under Interchange No. NCA2406, and the University of Notre Dame
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Arena, A.S., Nelson, R.C. Measurement of unsteady surface pressure on a slender wing undergoing a self-induced oscillation. Experiments in Fluids 16, 414–416 (1994). https://doi.org/10.1007/BF00202067
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DOI: https://doi.org/10.1007/BF00202067