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TECHNICAL PAPERS

Prediction of Blade-Vortex Interaction Airloads With Higher-Harmonic Pitch Controls Using the 2GCHAS Comprehensive Code

[+] Author and Article Information
Joon W. Lim, Chee Tung, Yung H. Yu

Army/NASA Rotorcraft Division, US Army AMCOM (AMRDEC), NASA Ames Research Center, Moffett Field, CA 94035

J. Pressure Vessel Technol 123(4), 469-474 (Jun 19, 2001) (6 pages) doi:10.1115/1.1401025 History: Received March 14, 2001; Revised June 19, 2001
Copyright © 2001 by ASME
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References

Yu, Y. H., Gmelin, B., Heller, H., Philippe, J. J., Mercker, E., and Preisser, J. S., 1994, “HHC Aeroacoustics Rotor Test at the DNW—The Joint German/French/US HART Project,” 20th European Rotorcraft Forum, Amsterdam, The Netherlands, Oct.
Gmelin, B., Heller, H., Mercker, E., Philippe, J. J., Preisser, J. S., and Yu, Y. H., 1995, “The HART Program, a Quadrilateral Cooperative Research Effort,” American Helicopter Society 51st Annual Forum, Fort Worth, TX, May.
Splettstoesser, W. R., Kube, R., Wagner, W., Seelhorst, U., Boutier, A., Micheli, F., Mercker, E., and Pengel, K., 1997, “Key Results from a Higher Harmonic Control Aeroacoustic Rotor Test (HART) in the German-Dutch Wind Tunnel,” J. Am. Helicopter Soc., 42 , No. 1, Jan.
Splettstoesser, W. R., Kube, R., Seelhorst, U., Wagner, W., Boutier, A., Micheli, F., Mercker, E., and Pengel, K., 1995, “Higher Harmonic Control Aeroacoustic Rotor Test (HART)—Test Documentation and Representative Results,” DLR Report No. DLR-IB-129-95/28, Braunschweig, Germany.
Tung, C., Gallman, J., Kube, R., Wagner, W., Van der Wall, B., Brooks, T., Burley, C., Boyd, D., Rahier, G., and Beaumier, P., 1995, “Prediction and Measurement of Blade-Vortex Interaction Loading,” 1st Joint CEAS/AIAA Aero-acoustics Conference, Munich, Germany, June.
Brooks, T., Boyd, D., Jr., Burley, C., and Jolly Jr., R, 1996, “Aeroacoustics Codes for Rotor Harmonic and BVI Noise—CAMRAD.Mod1/HIRES,” 2nd AIAA/CEAS Aeroacoustics Conference, State College, PA, May.
Beaumier, P. and Spiegel, P., 1995, “Validation of ONERA Aeroacoustic Prediction Methods for Blade-Vortex Interaction using HART Tests Results,” American Helicopter Society 51st Annual Forum, Fort Worth, TX, May.
Lim, J. W., and Tung, C., 1997, “2GCHAS Prediction of HART Blade-Vortex Interaction Loading,” American Helicopter Society Technical Specialists’ Meeting for Rotocraft Acoustics and Aerodynamics, Williamsburg, VA., Oct.
Wachspress, D. A., and Quackenbush, T. R., 1997, “Wake Model Requirements for Prediction of BVI Airloads,” American Helicopter Society Technical Specialists’ Meeting for Rotorcraft Acoustics and Aerodynamics, Williamsburg, VA., Oct.
Kube, R., Splettstoesser, W. R., Wagner, W., Seelhorst, U., Yu, Y. H., Tung, C., Beaumier, P., Prieur, J., Rahier, G., Spiegel, P., Boutier, A., Brooks, T. F., Burley, C. L., Boyd, D. D., Mercker, E., and Pengel, K., 1996, “HHC Aeroacoustic Rotor Tests in the German Dutch Wind Tunnel: Improving Physical Understanding and Prediction Codes,” American Helicopter Society 52nd Annual Forum, Washington, DC, May.
Beaumier, P., Prieur, J., Rahier, G., Demargne, Tung C., Gallman, J. M., Yu, Y. H., Kube, R., Van der Wall, B. G., Schultz, K. J., Splettstoesser, W. R., Brooks, T. F., Burley, C. L., and Boyd, D. D., 1994, “Effect of Higher Harmonic Control on Helicopter Rotor Blade-Vortex Interaction Noise and Initial Validation,” AGARD Conf. Proc., AGARD-CP-552, Berlin, Germany, Oct., pp. 26.1–26.21.
Anon, 2001, 2GCHAS Theory Manual, Version 3.0, Vols. I and II, U.S. Army Aeroflightdynamics Directorate, Aug.
Johnson, W., 1988, A Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics, Vol. 1—Theory Manual, Johnson Aeronautics, Palo Alto, CA.
Mercker, E., and Pengel, K., 1992, “Flow Visualization of Helicopter Blade Tip Vortices—A Qualitative Technique to Determine the Trajectory and the Position of the Tip Vortex Pattern of a Model Rotor,” 18th European Rotorcraft Forum, Avignon, France, Sept.

Figures

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2GCHAS aerodynamic model for the HART rotor blade consisting of 16 elements with a blade radius of 2 m
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Section lift predictions at an advance ratio of 0.15
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Section lift predictions using prescribed blade motion with measured data at an advance ratio of 0.15
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Effect of prescribed torsion with measured data on the section lift at an advance ratio of 0.15
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Effect of aerodynamic center on the section lift at an advance ratio of 0.15
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Effect of center of gravity on the section lift at an advance ratio of 0.15, assuming no aerodynamic center offset
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Predictions of lag and flap deflections at the blade tip at an advance ratio of 0.15 for Run 140 (BL)
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Prediction of elastic torsion deflection at the blade tip at an advance ratio of 0.15 for Run 140 (BL), Run 138 (MN), and Run 133 (MV)
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Effect of aerodynamic center on blade tip elastic torsion at an advance ratio of 0.15 for Run 140 (BL)
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Effect of center of gravity on blade tip elastic torsion at an advance ratio of 0.15 for Run 140 (BL)
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Comparison of the measured and predicted tip vortex filament locations at the azimuths of 35 and 295 deg—(a) BL case (Run 140), (b) MN case (Run 138), and (c) MV case (Run 133)

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