Fluent (IoA)

Aerodynamic DepartmentInstitute of Aviation

Adam DziubińskiCFD group

IoAIoA

FLUENT

Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009


Content

Fluent CFD softwareFluent CFD software1. Short description of main features of Fluent

Fluent CFD software

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



FLUENT- short review (1)

FLUENTTM is one of the products of ANSYS Inc

FLUENTTM is a powerful and flexible general purposeFLUENTTM is a powerful and flexible general-purpose computational fluid dynamics (CFD) package used for engineering simulations of all levels of complexity. It offers a

h i f h i l d l th t b li dcomprehensive range of physical models that can be applied to a broad range of industries and applicationsFLUENTTM basic features ( www.fluent.com/software/fluent/ )FLUENT basic features ( www.fluent.com/software/fluent/ ) Grids, Numerics & Parallel Processing Dynamic & Moving Mesh & Turbulence & Acoustics Reacting Flow Heat Transfer, Phase Change & Radiation, g Postprocessing Multiphase C t i d T l


Customized Tool


FLUENT- short review (2) Preprocessing

GAMBIT:GAMBIT: structure, unstructuredstructure, unstructuredand hybrid gridsand hybrid grids

structure grid

and hybrid grids,and hybrid grids,boundary layers subgridboundary layers subgrid

boundarylayer subgrid

unstructured grid

unstructured grid

TGRID:TGRID: unstructured grids,unstructured grids,by solver used also to gridby solver used also to gridadaptationadaptation

adaptation



FLUENT- short review (3) Solver

Fluid flow and heat transferFLUENTTM Available Models

momentum, continuity, energy equations

radiation Turbulence

(U)RANS: Spalart-Allmaras, k-ε (several models) k-ωk-ε (several models), k-ω, Reynolds stress;

Large-eddy simulation (LES) and detached eddy simulation (DES)and detached eddy simulation (DES)

Species transport Volumetric reaction Multiphase flows Moving and deforming mesh U d fi d l t t ti


User defined scalar transport equations Virtual blade model (VBM)


FLUENT- short review (4)

FLUENT™ software package has been designed to analyse the flowfield using Finite Volume Method (FVM)solution of Navier-Stokes equations.q

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)for viscosity phenomena modelling). Generation, which means taking into

account external forces influencing the flow (a pressure jump on a fan for example)


the flow (a pressure jump on a fan for example)


FLUENT- short review (5) User Defined Function and Postprocesor

UDF Code

Physical model with simplifications, to use with Fluent FAN model Applicationpp



FLUENT in CESAR Project

In CESAR project FULENTTM package was used in:

WP1 1 1 software validation for high lift system testingWP1.1.1 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 propellerWP3.3.1 aerodynamic characteristics calculation of propeller

airfoils – preprocessing of database for aerodynamicdesign of propeller blade (motivation: strong compressibility effects)


( g p y )


FLUENT- Airfoil with High Lift System

MS(1)-0317 MS(1)-0317 ith 35 d f l flwith 35 deg. fowler flapwith 35 deg. fowler flap



FLUENT- Airfoil with High Lift SystemFLUENT- Airfoil with High Lift SystemFLUENT- Airfoil with High Lift System

flap chord : 30% coverlap : 0% cgap : 3% c

MS(1)-0317 with 35 deg. flap

gap : 3% cextension : 16% cmain T.E. : 90% c

0

0.1

Z/C

0 0.25 0.5 0.75 1 1.25-0.2

-0.1

0


X/C



Comparison of resultsComparison of resultsComparison of results Comparison of results in different numeric codes. in different numeric codes.




Comparison between : WTT results and FLUENTWTT results and FLUENT

calculation using K-ε turbulence model.

Ai f ilAirfoil:MS(1)-0317 with 35 deg. flap

Re= 1.65*106 and Ma=0.15




ILL417 ILL417 with 30 and 40 fowler flapwith 30 and 40 fowler flap




Comparison of numerical solutions and WTT data

airfoil: ILL 415 with 30 deg flap

Ma = 0.1

Re = 1.14*106




Comparison of numerical solutions and WTT data

airfoil: ILL 415 with 40 deg flap

Ma = 0.1

Re = 1.14*106




Computational mesh example formesh example for ILL415 with 40 deg flap. Adaptaton to obtain “Y+” ~=40obtain Y+ ~=40 has been done.




V l it it d ILL415 ith 40 d flVelocity magnitude map on ILL415 with 40 deg flap

Alpha = 15 Alpha = 16 Alpha = 17


Alpha = 20Alpha =19Alpha = 18



ILM-115 ILM-115 i f ilairfoilairfoil



FLUENT- Airfoil ILM115

Validation of numerical results

airfoil: ILM 115airfoil: ILM 115

Ma = 0.61

Re = 2 66*106Re = 2.66*106



FLUENT- Airfoil ILM115

idgrid:43 908 cells model of turbulence:Spalart-Allmaras




AC-1 aircraftAC-1 aircraft



FLUENT- AC1 Aircraft

Alpha = 0.0 degp gMa = 0.35

CD=0.0562C =0 350CL=0.350CM=-0.066




Alpha = 0 0 degAlpha = 0.0 degMa = 0.35

CD=0.0562C 0 350CL=0.350CM=-0.066




Static pressure on surface

of AC-1 aircraft and two cuts

of normalized velocity vectors

k b hi d i


on a wake behind a wing.



simulation of engine influence including:

Propellers as a surfaces of pressure jump (blue pathlines) engine exhausts as


inlet (red pathlines)



ICEM CFD Tetra mesh:

1 307 853 Cells1 307 853 Cells

half mesh divided by aircraft's plane of symmetry.





Ansys ICEM CFD abilities in creation of nonstructural mesh



IoA recent worksIoA recent works



FLUENT- Helicopter Simulation

Analysis of dynamic stall– unsteady calculation– SCHEME and UDF procedures.SCHEME and UDF procedures.– moving mesh– sliding mesh– Spalart-Almaras turbulence modelp

CL

0.2

0.4

0.6

0.8

1.0

1.2

1.4

1.6

1.8

2.0

2.2

2.4

2.2

2.4

0=8°, S=10°, = 4.475 Hzsteady

M = 0.2Re = 2.237e6ILH412M-S = 0 + S*sin(2t)

2.2

2.4

0=8°, S=10°, = 4.475 Hzsteady

M = 0.3Re = 3.356e6ILH412M-S = 0 + S*sin(2t)

2 0

2.2

2.4

0=8°, S=10°, = 4.475 Hzsteady

M = 0.4Re = 4.474e6ILH412M-S = 0 + S*sin(2t)

-4 -2 0 2 4 6 8 10 12 14 16 18 20-0.6

-0.4

-0.2

0.0

CL

0.8

1.0

1.2

1.4

1.6

1.8

2.0 steady

CL

0.8

1.0

1.2

1.4

1.6

1.8

2.0 steady

CL

0 6

0.8

1.0

1.2

1.4

1.6

1.8

2.0 y

-4 -2 0 2 4 6 8 10 12 14 16 18 20

-0.4

-0.2

0.0

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0.6

-4 -2 0 2 4 6 8 10 12 14 16 18 20

-0.4

-0.2

0.0

0.2

0.4

0.6

-4 -2 0 2 4 6 8 10 12 14 16 18 20

-0.4

-0.2

0.0

0.2

0.4

0.6


Lift coefficient versus Angle of Attack - Influence of Mach Number



Design and optimisation of helicopter main rotor – flow field analysis in hover


blade tip vortex



Simulation of WSK PZLW-3 in hover over edge of the edge of the roofroof

M i t d t il tMain rotor and tail rotor are simulated using fan model




Simulation of WSK PZLW-3 in hover above the W 3 in hover above the Royal Castle in Warsaw

Main rotor and tail rotor are simulated using fan modelSt d l l ti


Steady calculation


Bye, Bye !!!

Thank you for your attention


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