2014
DOI: 10.1007/978-94-007-7049-2
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Unsteady Computational Fluid Dynamics in Aeronautics

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Cited by 68 publications
(68 citation statements)
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“…The first wall-normal grid point is located with non-dimensional wall distance y + 1 ≤ 1 across the domain ensuring sufficient resolution to capture the boundary layer. The non-dimensional streamwise and spanwise grid spacings are ∆x + ≈ 100 and ∆z + ≈ 35 respectively, in line with accepted empirical requirements (Tucker 2014).…”
Section: Aerodynamic Analysissupporting
confidence: 76%
“…The first wall-normal grid point is located with non-dimensional wall distance y + 1 ≤ 1 across the domain ensuring sufficient resolution to capture the boundary layer. The non-dimensional streamwise and spanwise grid spacings are ∆x + ≈ 100 and ∆z + ≈ 35 respectively, in line with accepted empirical requirements (Tucker 2014).…”
Section: Aerodynamic Analysissupporting
confidence: 76%
“…However, in the frame of a zonal treatment, the practitioner needs best practice guidelines as well as some basic a priori knowledge of the flow considered, such as whether it is a freeshear layer type flow, a purely wall-bounded type flow or a mixture of the two. The authors' position is now increasingly shared by other teams [14,17]. As an example, in the framework of turbomachinery applications, Tyacke et al [18] state that 'the expectation of producing a single modelling strategy that will work effectively and reliably for all engine zones is unrealistic'!…”
Section: A Glimpse At Advanced Simulations Of Unsteady Turbulent Flowmentioning
confidence: 99%
“…For the URANS model, a relatively coarse grid is utilized. The grid for the DDES model is created according to the grid resolution requirements from [17]. Regarding the time discretization, the second order fully implicit scheme is adopted, which has no stability problem when the CFL number is greater than 1 [11].…”
Section: Test Casementioning
confidence: 99%