Development of a three-dimensional icing simulation code in the NSMB flow solver

This study investigates the physical mechanisms of the use of Active Flow Control (AFC) associated with morphing through cambering approach in a high-lift wing-flap system. Results of high-fidelity numerical simulations are examined at high Reynolds number (Re/c) of 4.6 Million. Adapted turbulence models are used to capture the flow separation and the development of coherent structures. Different approaches of AFC are proposed to suppress the flow separation located approximately at 60% of the cambered flap's chord. The present study focuses on AFC using steady continuous jet, unsteady valves or oscillators (pulsed blowing) and more precisely the Zero Net Mass Flux (synthetic jet) with the blowing-suction approach. The AFC at an optimal velocity and frequency of actuation enabled an enforcement of the flow re-attachment and a delay of the flow separation. The minimum jet velocity and a feasible vibration frequency are discussed providing a practically complete control of the separation regarding the high deflection angle and cambering dimensions. As a main result of the study, the pressure distribution is enhanced over both wing-flap surfaces, adverse pressure gradients are suppressed and the re-attachment of the boundary layer is obtained. These results have the potential to increase significantly the aerodynamic efficiency of aircraft during the take-off and landing phases.

show abstract

“…A variety of papers have been published on NSMB, examples are in Refs. [9][10][11][12][13][14][15][16][17][18][19].…”

Section: Nsmb Cfd Solver and Numerical Methodsmentioning

confidence: 99%

Unsteady CFD simulations for Active Flow Control

Marouf

Chouippe

Vos

et al. 2021

Aiaa Aviation 2021 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…In previous papers [23,10], we developed and validated an icing simulation code in the NSMB flow solver. The Ice solver consisted of four modules: compressible air solver, Eulerian droplet solver, SWIM solver, ALE grid regeneration module.…”

Section: Introductionmentioning

confidence: 99%

Multi-Step Ice Accretion Simulation Using the Level-Set Method

Al-Kebsi¹,

Mosé²,

Hoarau³

2019

SAE Technical Paper Series

Self Cite

View full text Add to dashboard Cite

Ice accumulation in aircraft is modelled using the Level-Set (LS) method. Current two-dimensional and threedimensional icing models are limited regarding complex re-meshing due to ice accretion. The Level-Set method allows fully multi-step simulation of ice accretion. The solid boundary is treated implicitly or explicitly. The solid body can be defined via a characteristic level set function in the former case, and as a layer or list of points in the later. Consequently, the boundary conditions for the airflow are applied through a penalization term, or by direct forcing. Correspondingly, the droplet transport is computed using an Eulerian approach in an Immersed Boundary Method (IBM) coupled with Level-Set (IBM-LS) framework, in which the droplet fields impinge on an explicit layer of cells defined by the LS function using a discrete IBM formulation of the interface.

show abstract

“…In a previous paper (Pena et al (2015)), a three-dimensional icing code has been developed and validated in the NSMB (Navier-Stokes-Multi-Block) flow solver. The icing code implemented consists of an Eulerian droplet transport equations and an iterative Messinger model.…”

Section: Introductionmentioning

confidence: 99%

A single step ice accretion model using Level-Set method

Pena

Hoarau

Laurendeau

2016

Journal of Fluids and Structures

Self Cite

View full text Add to dashboard Cite

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.

show abstract

Development of a three-dimensional icing simulation code in the NSMB flow solver

Cited by 9 publications

References 17 publications

Unsteady CFD simulations for Active Flow Control

Unsteady CFD simulations for Active Flow Control

Multi-Step Ice Accretion Simulation Using the Level-Set Method

A single step ice accretion model using Level-Set method

Contact Info

Product

Resources

About