In-flight icing simulation for two-dimensional configurations

2020 ◽  
Vol 34 (14n16) ◽  
pp. 2040068
Author(s):  
Tong Liu ◽  
Jin-Sheng Cai ◽  
Kun Qu ◽  
Shu-Cheng Pan
Keyword(s):  
Navier Stokes ◽  
Simulation Tool ◽  
Two Dimensional ◽  
Ice Accretion ◽  
Aircraft Icing ◽  
Droplet Impingement ◽  
Droplet Flow ◽  
Accretion Model ◽  
Median Volume ◽  
Naca 0012

This paper presents a comprehensive aircraft icing simulation tool implemented in an in-house Navier–Stokes parallel multi-block solver. In detail, the droplet flow field is solved by Eulerian approach, and a Partial Differential Equation (PDE)-based ice accretion model is adopted to determine the runback water flow and icing rate. Numerical validations are performed on the two-dimensional (2D) NACA 0012 airfoil, where good agreements with the literature are observed. Additionally, the paper investigates the influence of droplet size on the final ice shape. Results show that droplets with greater Median Volume Diameter (MVD) are more likely to impact on the wall, which results in larger droplet impingement limit and icing limit.

Numerical Analysis of Ice Accretion and Icing Effects on Airfoils

2012 ◽  
Vol 249-250 ◽  
pp. 40-45
Author(s):  
Bo An ◽  
Wei Min Sang
Keyword(s):  
Stokes Equations ◽  
Leading Edge ◽  
Integral Form ◽  
Navier Stokes ◽  
Ice Accretion ◽  
Aircraft Icing ◽  
Navier Stokes Equations ◽  
Runge Kutta Method ◽  
Cfd Method ◽  
Naca 0012

Aircraft icing cause significant degradation in aerodynamics performance and flight safety. Numerical methods are developed and presented to simulate two icing-related problems for airfoils, namely ice accretion and icing effects. Ice accretion on the leading edge of the NACA 0012 airfoil is predicted using CFD method based on spring analogy. A four-order Runge-Kutta method is used to solve the droplet trajectory equation. Besides, we use the integral form of Navier-Stokes equations and the Spalart-Allmaras turbulence model to study the icing effects. Designing three different icing models, the flow fields are analyzed. The results are in good agreement with the experimental data and show preliminarily that numerical method is feasible and effective.

Ice Accretion of Glaze Loads Model on Wires of Power Transmission Lines

2011 ◽  
Vol 189-193 ◽  
pp. 3225-3229
Author(s):  
Chun Cheng Liu ◽  
Jiao Liu
Keyword(s):  
Wind Speed ◽  
Transmission Lines ◽  
Prediction Models ◽  
Power Transmission ◽  
Time Dependent ◽  
Ice Accretion ◽  
Power Transmission Lines ◽  
Collision Efficiency ◽  
Accretion Model ◽  
Median Volume

In connection with the process of glaze ice, prediction models about height and thickness of ice coating under uniform and non-uniform ice accretion of wire are presented by taking into account local collision efficiency, freeze coefficient and collection coefficient based on the existing model at home and abroad. The time-dependent ice models on the conditions of different median volume diameter of super-cooled droplets, wind speed and wire diameter are analyzed. Compared with the existing model, the proposed ice accretion model performed well in predicting ice’s weight and thickness. At the same time, it can give some lights on ice disaster and anti-icing design for power transmission lines.

Multi-Layer Stochastic Ice Accretion Model for Aircraft Icing

2021 ◽  
Author(s):  
Helene Papillon Laroche ◽  
Simon Bourgault-Cote ◽  
Eric Laurendeau
Keyword(s):  
Ice Accretion ◽  
Aircraft Icing ◽  
Accretion Model

Computational Evaluation of the Periodic Performance of a NACA 0012 Fitted With a Gurney Flap

2001 ◽  
Vol 124 (1) ◽  
pp. 227-234 ◽  
Author(s):  
James C. Date ◽  
Stephen R. Turnock
Keyword(s):  
Vortex Shedding ◽  
Navier Stokes ◽  
Two Dimensional ◽  
Time Step ◽  
Computational Evaluation ◽  
Gurney Flap ◽  
Section Design ◽  
Computationally Intensive ◽  
Lift And Drag ◽  
Naca 0012

A detailed computational investigation into the periodic two-dimensional performance of a NACA 0012 section fitted with 2 and 4 percent h/c Gurney flaps operating at a Reynolds number of 0.85×106 is presented. The aim of the work was to determine the suitability of the incompressible Reynolds-averaged Navier-Stokes (RANS) formulation in modeling the vortex shedding experienced by lifting sections with blunt, sharp edged features. In particular, whether under-converged steady state calculations could be used for section design performance evaluation in place of the computationally intensive time accurate flow simulations. Steady, periodic, and time-averaged two-dimensional lift and drag coefficients, as well as vortex shedding frequency, were predicted and compared with the available experimental data. Reasonable agreement was found, once sufficiently fine grids had been generated, and the correct time step determined for the time accurate simulations.

scholarly journals A New Ice Accretion Model for Aircraft Icing Based on Phase-Field Method

2021 ◽  
Vol 11 (12) ◽  
pp. 5693
Author(s):  
Hao Dai ◽  
Chunling Zhu ◽  
Huanyu Zhao ◽  
Senyun Liu
Keyword(s):  
Phase Field ◽  
Mass Conservation ◽  
Simulation Method ◽  
Field Method ◽  
Phase Field Method ◽  
Ice Accretion ◽  
Aircraft Icing ◽  
Phase Equation ◽  
Accretion Model ◽  
Ice Conditions

Aircraft icing presents a serious threat to the aerodynamic performance and safety of aircraft. The numerical simulation method for the accurate prediction of icing shape is an important method to evaluate icing hazards and develop aircraft icing protection systems. Referring to the phase-field method, a new ice accretion mathematical model is developed to predict the ice shape. The mass fraction of ice in the mixture is selected as the phase parameter, and the phase equation is established with a freezing coefficient. Meanwhile, the mixture thickness and temperature are determined by combining mass conservation and energy balance. Ice accretions are simulated under typical ice conditions, including rime ice, glaze ice and mixed ice, and the ice shape and its characteristics are analyzed and compared with those provided by experiments and LEWICE. The results show that the phase-field ice accretion model can predict the ice shape under different icing conditions, especially reflecting some main characteristics of glaze ice.

An Eulerian Method for Water Droplet Impingement by Means of an Immersed Boundary Technique

2012 ◽  
Author(s):  
F. Capizzano ◽  
E. Iuliano
Keyword(s):  
Water Droplet ◽  
Numerical Solutions ◽  
Three Dimensional ◽  
Immersed Boundary ◽  
Test Cases ◽  
Simulation Tool ◽  
Ice Accretion ◽  
Droplet Impingement ◽  
Eulerian Methods ◽  
Numerical Approaches

The estimation of water droplet impingement is the first step for a complete ice-accretion assessment. Basically two different numerical approaches can be found in literature: the Lagrangian and the Eulerian methods. The present paper describes the design and development of a water impingement simulation tool based on Eulerian droplet equations solved on Cartesian meshes by using an immersed boundary (IB) technique. The robustness of the methodology and the accuracy of the approach are discussed. The method is applying to classical two- and three-dimensional test-cases for which experimental data are available in literature. The results will be discussed by comparing with experimental and body-fitted numerical solutions.

Unsteady RANS Computations of the Flow Past an Airfoil in the Wake of a Rod

2002 ◽  
Author(s):  
Je´roˆme Boudet ◽  
Damiano Casalino ◽  
Marc C. Jacob ◽  
Pascal Ferrand
Keyword(s):  
Vortex Shedding ◽  
Turbulence Models ◽  
Leading Edge ◽  
Navier Stokes ◽  
Two Dimensional ◽  
Vorticity Field ◽  
Unsteady Rans ◽  
Variable Configuration ◽  
Naca 0012 ◽  
Insight Into

Two-dimensional Reynolds Averaged Navier-Stokes (RANS) equations are solved in order to simulate the interaction between a Ka´rma´n vortex street shed from a rod and a NACA-0012 airfoil in the wake of the rod. Two closure turbulence models are tested, a linear and a nonlinear k-ω model, for a chord based Reynolds number Rec ∼ 4.8105. These models provide consistent results in terms of both mean and fluctuating flow quantities. Insight into the instantaneous vorticity field shows that the vortex shedding pattern near the wall is quite well predicted, despite an over-estimated frequency. Downstream, computations always exhibit head-on interactions of the vortices with the airfoil leading edge whereas the experiments show a more variable configuration.

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