Numerical simulation of icing effect and ice accretion on three-dimensional configurations

Sang, Weimin; Shi, Yu; Xi, Chao

doi:10.1007/s11431-013-5277-3

Cited by 18 publications

(9 citation statements)

References 23 publications

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“…Identical results were obtained along wing span partially validating the three-dimensional implementation. Impingement curves are plotted on three sections A, B & C respectively at 20%, 60% and 90% of span length and compared with Lagrangian results from Sang et al 102 in Fig. 23.…”

Section: Vc Resultsmentioning

confidence: 99%

Recent Developments of the Navier Stokes Multi Block (NSMB) CFD solver

Hoarau

Pena

Vos

et al. 2016

54th AIAA Aerospace Sciences Meeting

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Section: Vc Resultsmentioning

confidence: 99%

Recent Developments of the Navier Stokes Multi Block (NSMB) CFD solver

Hoarau

Pena

Vos

et al. 2016

54th AIAA Aerospace Sciences Meeting

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“…The solutions were considered as converged when the residuals reached their minimum values after falling for more than five orders of magnitude [36], and the difference between the mass flow flux dropped below 0.001 kg•s −1 .…”

Section: Methodsmentioning

confidence: 99%

Design and aerodynamic investigation of a parallel vehicle on a wide-speed range

Huang

Wang

et al. 2014

Sci. China Inf. Sci.

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In order to design a hypersonic vehicle for a wide-ranged Mach number, a novel parallel vehicle for a wide-speed range has been proposed. In this paper, we employ a numerical method to investigate a parallel vehicle's aerodynamic performance and flow field characteristics. The obtained results show that the aerodynamic performance of the novel parallel vehicle is better than that of the waverider designed with a single Mach number for the wide-speed range. With the increase in Mach number, the lift-to-drag ratio of the novel parallel vehicle first increases and then decreases. When the Mach number is 7 and the angle of attack is 3 • , the lift-to-drag ratio is the largest, and its value is 3.968. When the angle of attack is 3 • , the lift-to-drag ratio is not lower than 3.786 in the range considered in the current study, and the novel parallel vehicle's aerodynamic performance is good. The wing changes the drag performance of the parallel vehicle remarkably, and results in the decrease of the lift-to-drag ratio. Meanwhile, the wing can enhance the pitching moment performance.

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“…Impingement curves are plotted on sections A, B & C respectively at 20%, 60% and 90% of span length and compared with Sang et al (2013) in Fig. 13.…”

Section: Case 2 : Naca0012mentioning

confidence: 99%

A single step ice accretion model using Level-Set method

Pena

Hoarau

Laurendeau

2016

Journal of Fluids and Structures

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A new approach using the Level-Set framework is developed in the NSMB (Navier-Stokes Multi-Block) compressible solver for modeling the ice/air interface evolution through time during in-flight icing. Droplet distribution and impingement efficiency are computed by an Eulerian approach and the accreted ice is calculated by a PDE model. An icing velocity field is introduced and the Level-Set equations are solved on body-fitted multi-block structured grids. The whole process is parallelized with the MPI library for efficient calculations. Single step icing is simulated on NACA23012 and NACA0012 airfoils and on the ONERA-M6 and the GLC-305 swept wings. In all the studied cases, the results are in good agreement with existing and available data validating the feasibility of the approach.

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Numerical simulation of icing effect and ice accretion on three-dimensional configurations

Cited by 18 publications

References 23 publications

Recent Developments of the Navier Stokes Multi Block (NSMB) CFD solver

Recent Developments of the Navier Stokes Multi Block (NSMB) CFD solver

Design and aerodynamic investigation of a parallel vehicle on a wide-speed range

A single step ice accretion model using Level-Set method

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