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CFD TAU Applications within the Airbus Aerodynamic Design Process

Presentation Voith Engineering Services | October 18 & 19 | 1

TAU User Meeting 18th & 19th October 2011

Process

Daniel Schulzewith contribution of Urs Baumgartl & Tim Onnenberg

� Company Introduction

Content


Presentation CeBeNetwork, Oktober 11

� TAU Application Areas

� Examples of TAU Studies

� Overall Conclusions

Paper ServiceMobilityEnergy

Company IntroductionAerospace within the Voith Group


Process Services

EngineeringServices

Facility Services America

Industrial Services Asia

Facility Services Europe

Process Industries

Aerospace Road & RailProfessional

Staffing

� Flight Physics

� Structure

Company IntroductionBusiness Units within Voith - Aerospace


� Systems, Cabin & Cargo

� Processes, Methods & Tools

� Technical Product Services

� Aerodynamics & Wind Tunnel Testing

� Computational Fluid Dynamics (CFD)

� Flight Dynamics

� Mass Properties

� Component Loads

� Aeroelastics

� UAV Design & Analysis

� Model Prototyping & Manufacturing

Company IntroductionSkill Groups within Voith Aerospace Flight Physics


Madrid (ES)

15

Madrid (ES)

15

Germany

Bremen 27

Hamburg 23

Germany

Bremen 27

Hamburg 23

Bristol (UK)

13

Bristol (UK)

13

Company IntroductionFlight Physics Engineers at Various Sites


1515

Toulouse (F)

5

Toulouse (F)

5 Bangalore (INDIA)

17

Bangalore (INDIA)

17

Voith FPY supports Airbus� Aerodynamic Design for:

• Clean Wing• High-Lift Devices• Fuselage & Tails

Application AreasOverview


• Fuselage & Tails• Air Systems

� Methods and Tools� Data for Loads

Each application area differs in1. Meshing strategies (dependant on e.g.

components and relevant flight conditions)2. Use of different TAU features

Application AreasClean Wing Design

� Simulation of cruise andlow speed performance

� Prediction of Mach and


� Prediction of Mach andlow speed buffet

� Prediction of transitionlocation

TAU with coupled Transition prediction is used to analyse the modified airfoil with regard to

� reducing wave drag

Clean Wing DesignLaminar Airfoil Modification

� reference� modified


� reducing wave drag

� maintain laminar length

� establish a robust boundary layer- - NCF� NTS

For short range missions the wing has to maintain a long laminar length at a variety

Clean Wing DesignComputation with coupled Transition Prediction


CL

• Analysis of cruise performance with regards to transition location• Used within the design process to increase the laminar region

near buffetdesign point

length at a variety of speeds, altitudes and weights.

� Comprehensive 2D studies for shape and setting design in early state of design process

� 3D computations for• Comparison to experimental data

− Calibration of simulation

Application AreasHigh-Lift Design


− Calibration of simulation method

− Understanding of flow features• Prediction of flow conditions for

− Differences in lift (and drag) performance

− Stall pattern− Component loads

� Prediction of particle trajectories and impingement

High-Lift Design2D shape and setting design studies

2D TAU SAe computations over representative spanwise sections cover wide range of high-lift shape and setting design in early state of process.


High-Lift DesignComparison of CFD with Wind Tunnel Results


Flow phenomena at the vicinity of maximum liftSeparation pattern: onset of tip separation while approaching maximum lift

Particle tracer module was used for trajectory computations. A comprehensive study allowed generic predictions about trajectory dependencies of various parameters:

� Flap deflection (circulation)

High-Lift DesignTrajectory Predictions

light particles


� Flap deflection (circulation)� Krueger deployment angle� Particle inertia parameter� Mach number� Angle of attack

heavy particles

TAU Particle Tracer Module

ne

ed

ed

se

ttin

g h

eig

ht

for

shie

ldin

g

10m/s

5m/s

15m/s

20m/s

impact velocity

∆∆∆∆dF

∆∆∆∆Ma

High-Lift DesignTrajectory Predictions (2)


TAU Particle Tracer Module

Implementation of parameters• impact angle• impact velocity allowed a more quantitative prediction of impact condition.

� consideration of non critical impingements possible

0 5 10 15 20

ne

ed

ed

se

ttin

g h

eig

ht

for

shie

ldin

g

impact angle

10m/s

5m/s

15m/s20m/s

Application AreasFuselage & Tails Design

3D computations for� Comparison to experimental data

• Calibration of simulation method


method• Understanding of flow

features� Prediction of flow conditions for

• Differences in lift, drag and sideforce

• Stall pattern

Objective:� Rear fuselage shaping study to achieve a shape with best suitable aerodynamic characteristics� Actuator disc computations for

Fuselage & Tails DesignRear Fuselage Design Study

cp


� Actuator disc computations for power effect on rear fuselage and tail planes� Clearance of blade tip to fuselage boundary layer� prediction of flow pattern in the vicinity of prop discs

boundary layer thickness� clearance of blade tip proofed

Visualisation of flow pattern in the vicinity of prop discs

Mac

h

Fuselage & Tails DesignRear Fuselage Design Study (2)


� clearance of blade tip proofed

boun

dary

laye

r th

ickn

ess

cp

Application AreasAir Systems Design

� Internal (and external) flow computations

� Prediction of drag and thrust recovery


� Proof of interface flow conditions for internal air systems

� Component Loads

� Prediction of surface temperatures

Air Systems DesignOptimisation of a RAM Air Outlet

OutletInlet


MixerBleed Air

Heat Exchanger

Pre-Cooler

50 %230°C, 3bar

~25°C

0°C, ~Cabinpressure

Q=m*∆∆∆∆T*Cp

Outer flow Outer flow

50 %

Modifications at Diffusor and Flap

� Smoothed rearward edge of diffusor� Displacement of cooling-film exhaust

Air Systems DesignOptimisation of a RAM Air Outlet (2)


� Increased thrust, increased mass flow� Higher velocities at outlet

� Reduced flap length and angle

� Reduced drag

� Expertise in the whole CFD-Process chain, i.e.CAD Preparation � Mesh Generation � CFD Solution � Analysis

� Meshing with Centaur; mesh generation strategy dependent upon a/c component studied

� Application of Mesh “Module Boxes”� Power On/Off Computations (Engine and/or Actuator Disc)

Overall ConclusionsCFD Expertise and Capabilities based on TAU


� Power On/Off Computations (Engine and/or Actuator Disc)� External and Internal Viscous Flow Computations� TAU with coupled Transition Prediction� TAU Particle Tracer Module

� Methods and Tool Development– Process chains for the heterogeneous HPC Cluster of Airbus– TAU development with R&T projects

(e.g. “smooth_taugrid”)– Tools for Aerodata for Loads (e.g. “InvesT”)

Thank you for your attention!


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