Some aircraft have exhibited a noticeable vibration and aero-acoustic phenomenon inside the nose landing gear cavity. The goal of the present study was to determine whether unsteady CFD using either unsteady RANS or detached eddy simulation (DES) could predict the cavity oscillation that was measured in a Boeing wind tunnel test. In general the agreement between the experiment and CFD was good. The CFD predicted an aircraft scale cavity tone frequency of 17 Hz compared to the measured value of 15 Hz. As well, the CFD predicted sound pressure level of the tone was within 4 dB of the measurements. From the present results it would appear that CFD can be used as a tool to investigate and possibly mitigate nose gear cavity tone mechanisms on new aircraft designs.
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Acknowledgments
The authors would like to thank the NASA Advanced Supercomputing Division (NAS) for donating the computing time on the Columbia supercomputer. As well we would like to thank Metacomp Technologies Inc. for all of their help with the CFD + + setup on Columbia. Finally the authors would like to thank Cyrille Breard, John Rose, Srini Bhat and Bill Simmons of the Boeing Company for all of their help with the problem setup and experimental data.
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Langtry, R., Spalart, P. (2009). Detached Eddy Simulation of a Nose Landing-Gear Cavity. In: Braza, M., Hourigan, K. (eds) IUTAM Symposium on Unsteady Separated Flows and their Control. IUTAM Bookseries, vol 14. Springer, Dordrecht. https://doi.org/10.1007/978-1-4020-9898-7_31
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