Extending a Three-Dimensional GPU RANS Solver for Unsteady Grid Motion and Free-Wake Coupling

Jude, Dylan; Baeder, James D.

doi:10.2514/6.2016-1811

Cited by 21 publications

(2 citation statements)

References 8 publications

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“…The CFD analysis is based on Reynolds-Averaged Navier-Stokes (RANS) and performed using the Mercury framework [8]. This framework is a multi-mesh multisolver which uses the Graphics Processing Unit Accelerated Rotor Flow Field Solver (GARFIELD) [9] and Hamiltonian Strand solver (HAMSTR) [10] in order to solve discretized overset grid systems.…”

Section: Cfd Solversmentioning

confidence: 99%

Aeroacoustic Analysis of Asymmetric Lift-Offset Helicopter in Forward Flight

Arias¹,

Baeder²,

Jung³

2021

Proceedings of the Vertical Flight Society 77th Annual Forum

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In recent years, the University of Maryland has worked on an asymmetric lift-offset compound helicopter. The configuration consists of a single main rotor helicopter with the addition of two key ways to increase the forward speed: a stubbed wing on the retreating fuselage side, and a slowed down rotor. Experiments and simulations have shown that the novel concept provides improved thrust potential and lift-to-drag ratios in high-speed forward flight. This study aims to determine whether the asymmetric lift-offset configuration also provides aeroacoustic benefits in forward flight in addition to its aerodynamic advantages. The aerodynamic results from previous computational and experimental studies are recreated using the Mercury framework, an in-house CFD solver based on Reynolds-Averaged NavierStokes (RANS). The acoustic analysis is performed using an acoustic code based on the Ffowcs William-Hawkings equation to solve for the noise propagating from the surfaces of the aircraft. It was found that for an advance ratio of 0.5 the wing-lift offset configuration can produce 56.8% more thrust at the same collective angle without any penalties in total noise. When the configurations produce equal thrust it was found that the wing-lift offset case has a 4 dB reduction in maximum overall sound pressure level. At an advance ratio of 0.3 with trim for equivalent thrust between configurations, a 3 dB maximum OASPL reduction was obtained with the inclusion of the wing.

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Section: Cfd Solversmentioning

confidence: 99%

Aeroacoustic Analysis of Asymmetric Lift-Offset Helicopter in Forward Flight

Arias¹,

Baeder²,

Jung³

2021

Proceedings of the Vertical Flight Society 77th Annual Forum

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“…They achieved an acceleration of 20x for the Euler equations. Additionally, several recent CFD applications can be seen in Wang, Abel, and Kaehler (2010); Xian and Takayuki (2011); Karantasis, Polychronopoulos, and Ekaterinaris (2014); Ma, Wang, and Pu (2014); Liu, Zhong, and Xu (2016), and Jude and Baeder (2016).…”

Section: Introductionmentioning

confidence: 99%

An implementation of the direct-forcing immersed boundary method using GPU power

Tutkun

Edis

2016

Engineering Applications of Computational Fluid Mechanics

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A graphics processing unit (GPU) is utilized to apply the direct-forcing immersed boundary method. The code running on the GPU is generated with the help of the Compute Unified Device Architecture (CUDA). The first and second spatial derivatives of the incompressible Navier-Stokes equations are discretized by the sixth-order central compact finite-difference schemes. Two flow fields are simulated. The first test case is the simulated flow around a square cylinder, with the results providing good estimations of the wake region mechanics and vortex shedding. The second test case is the simulated flow around a circular cylinder. This case was selected to better understand the effects of sharp corners on the force coefficients. It was observed that the estimation of the force coefficients did not result in any troubles in the case of a circular cylinder. Additionally, the performance values obtained for the calculation time for the solution of the Poisson equation are compared with the values for other CPUs and GPUs from the literature. Consequently, approximately 3× and 20× speedups are achieved in comparison with GPU (using CUSP library) and CPU, respectively. CUSP is an open-source library for sparse linear algebra and graph computations on CUDA.

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