Aerodynamic Department Institute of Aviation. Adam Dziubiński CFD group FLUENT

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1 Adam Dziubiński CFD group IoA FLUENT

2 Content Fluent CFD software 1. Short description of main features of Fluent 2. Examples of usage in CESAR Analysis of flow around an airfoil with a flap: VZLU + ILL4xx validation with experimental data Analysis of flow aroundilm155 airfoil validation with experimental data Example of 3D modelling evector aircraft 3. Examples of fluent usage in IoA CFD group recent works. 4. EOF

3 FLUENT- short review (1) FLUENT TM is one of the products of ANSYS Inc FLUENT TM is a powerful and flexible general-purpose computational fluid dynamics (CFD) package used for engineering simulations of all levels of complexity. It offers a comprehensive range of physical models that t can be applied to a broad range of industries and applications FLUENT TM basic features ( ) Grids, Numerics & Parallel Processing Dynamic & Moving Mesh Turbulence & Acoustics Reacting Flow Heat Transfer, Phase Change & Radiation Postprocessing Multiphase Customized Tool

4 GAMBIT: structure, unstructured and hybrid grids, boundary layers subgrid structure grid FLUENT- short review (2) Preprocessing boundary layer subgrid unstructured grid unstructured grid TGRID: unstructured grids, by solver used also to grid adaptation adaptation

5 FLUENT- short review (3) Solver FLUENT TM Available Models Fluid flow and heat transfer momentum, continuity, energy equations radiation Turbulence (U)RANS: Spalart-Allmaras, k-ε (several models), k-ω, Reynolds stress; Large-eddy simulation (LES) and detached eddy simulation (DES) Species transport Volumetric reaction Multiphase flows Moving and deforming mesh User defined d scalar transport t equations Virtual blade model (VBM)

6 FLUENT- short review (4) FLUENT software package has been designed to analyse the flowfield using Finite Volume Method (FVM) solution of Navier-Stokes equations. Movement of fluid in domain is described by Navier Stokes set of equations, following parts of equation are responsible for : Unsteady flow description Convection, flow caused by buoyancy effect. Diffusion of disturbances (this part is responsible for viscosity phenomena modelling). Generation, which means taking into account external forces influencing the flow (a pressure jump on a fan for example)

7 FLUENT- short review (5) User Defined Function and Postprocesor UDF Code Physical model with simplifications, to use with Fluent FAN model Application

8 FLUENT in CESAR Project In CESAR project FULENT TM package was used in: WP software validation for high lift system testing WP1.2.1 additional analysis in design and optimisation of turbulent airfoil process to evaluate flowfield in selected flow condition (motivation: strong compressibility effects, separation on high angles of attack) WP1.2.2 additional analysis in design and optimisation of turbulent wing process to evaluate flowfield in selected flow condition (motivation: strong compressibility effects, separation on high angles of attack) WP3.3.1 aerodynamic characteristics calculation of propeller airfoils preprocessing of database for aerodynamic design of propeller blade (motivation: strong compressibility effects)

9 FLUENT- Airfoil with High Lift System MS(1)-0317 with 35 deg. fowler flap

10 FLUENT- Airfoil with High Lift System MS(1)-0317 with 35 deg. flap flap chord : 30% c overlap : 0% c gap : 3% c extension : 16% c main T.E. : 90% c 0.1 Z/C X/C

11 Comparison of results in different numeric codes. FLUENT- Airfoil with High Lift System

12 FLUENT- Airfoil with High Lift System Comparison between : WTT results and FLUENT calculation using K-ε turbulence model. Airfoil: il MS(1)-0317 with 35 deg. flap Re= 1.65*10 6 and Ma=0.15

13 FLUENT- Airfoil with High Lift System ILL417 with 30 and 40 fowler flap

14 FLUENT- Airfoil with High Lift System Comparison of numerical solutions and WTT data airfoil: ILL 415 with 30 deg flap Ma = 0.1 Re = 1.14*10 6

15 FLUENT- Airfoil with High Lift System Comparison of numerical solutions and WTT data airfoil: ILL 415 with 40 deg flap Ma = 0.1 Re = 1.14*10 6

16 FLUENT- Airfoil with High Lift System Computational mesh example for ILL415 with 40 deg flap. Adaptaton to obtain Y+ ~=40 has been done.

17 FLUENT- Airfoil with High Lift System Velocity magnitude map on ILL415 with 40 deg flap Alpha = 15 Alpha = 16 Alpha = 17 Alpha = 18 Alpha =19 Alpha = 20

18 FLUENT- Airfoil with High Lift System ILM-115 airfoil if il

19 FLUENT- Airfoil ILM115 Validation of numerical results airfoil: ILM 115 Ma = 0.61 Re = 2.66*10 6

20 FLUENT- Airfoil ILM115 grid: cells model of turbulence: Spalart-Allmaras

21 FLUENT- Airfoil with High Lift System AC-1 aircraft

22 FLUENT- AC1 Aircraft Alpha = 0.0 deg Ma = 0.35 C D = C L =0.350 C M =-0.066

23 FLUENT- AC1 Aircraft Alpha = 0.00 deg Ma = 0.35 C D = C L =0.350 C M =-0.066

24 FLUENT- AC1 Aircraft Static pressure on surface of AC-1 aircraft and two cuts of normalized velocity vectors on a wake behind a wing.

25 FLUENT- AC1 Aircraft simulation of engine influence including: Propellers as a surfaces of pressure jump (blue pathlines) engine exhausts as inlet (red pathlines)

26 FLUENT- AC1 Aircraft ICEM CFD Tetra mesh: Cells half mesh divided by aircraft's plane of symmetry.

27 FLUENT- AC1 Aircraft Ansys ICEM CFD abilities in creation of nonstructural mesh

28 FLUENT- Airfoil with High Lift System IoA recent works

29 FLUENT- Helicopter Simulation Analysis of dynamic stall unsteady calculation SCHEME and UDF procedures. moving mesh sliding mesh Spalart-Almaras turbulence model C L C L M = 0.2 ILH412M-S Re = 2.237e6 = 0 + S *sin(2 t) =8, S =10, =4.475Hz 2.0 steady C L 2.4 ILH412M-S M = 0.3 Re = 3.356e6 = 0 + S *sin(2 t) =8, S =10, =4.475Hz 2.0 steady C L M = 0.4 ILH412M-S Re = 4.474e6 = 0 + S *sin(2 t) =8, S =10, =4.475Hz 2.0 steady Lift coefficient versus Angle of Attack - Influence of Mach Number

30 FLUENT- Helicopter Simulation

31 FLUENT- Helicopter Simulation Design and optimisation of helicopter main rotor flow field analysis in hover blade tip vortex

32 FLUENT- Helicopter Simulation Simulation of WSK PZL W-3 in hover over edge of the roof Main rotor and tail rotor are simulated using fan model

33 FLUENT- Helicopter Simulation Simulation of WSK PZL W-3 in hover above the Royal Castle in Warsaw Main rotor and tail rotor are simulated using fan model Steady calculation l

34 Bye, Bye!!! Thank you for your attention

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