aeroelastic analysis of a wing (pressentation)
DESCRIPTION
This pressentation will show you how to carry out Aeroelastic analysis in ANSYSTRANSCRIPT
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Aeroelastic Analysis of a Reference
Aircraft Wing for Investigation of Structural Stability using ANSYS®
Student: Advisor : S/L Nadeem
Muhammad Amir Co-Advisor : S/L Kashif
Pak No. 71008
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SCOPE
A Reference Aircraft Wing shallbe Investigated for its StructuralStability by Performing Fluid-Structure Interaction Studies,using ANSYS as ComputationalPlatform.
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MILESTONES
Two-Way FSI in ANSYS Workbench
Static Aeroelastic Analysis to Compute
Divergence Speed
Dynamic Aeroelastic Analysis and
Calculating Flutter Boundary
Validation of Divergence Speed
and Flutter Boundary
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METHODOLOGY
Literature Review and Software Learning
Demonstration of Two-way FSI
Material Properties and Flow Characteristics
Discretization of Structural and Aerodynamic domains
Static Aeroelastic Analysis
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METHODOLOGY
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Dynamic Aeroelastic Analysis
Results and Discussion on StabilityParameters
Conclusion
Recommendations
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Aeroelasticity and ANSYS 13
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A Coupled Field
– No flexibility, No Aeroelasticity
– Max Wingtip Displacement of Boeing 747=24 ft
Serious Threat to Flight Safety
Aeroelasticity
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Aeroelasticity
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Static Aeroelastic Phenomena• Wing Divergence
• Control Reversal
Dynamic Aeroelastic phenomena• Flutter
• Limit Cycle Oscillation
• Gust Response
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Flutter
Highly Non-linear Phenomena
Experimental Tests are Destructive
Analytical Results not Possible
Best Option is Finite Element Method
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ANSYS 13
ANSYS 13 Capabilities....
Flow Analysis: CFX/Fluent
Meshing: ICEM CFD
Two Way FSI: Multi-field Solver
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ANSYS 13
One Way FSI
ANSYS MECHANICAL-
FLUENT/CFX
Two Way FSI
ANSYS MECHANICAL-
CFX
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TWO WAY FSI
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DEMONSTRATION OF TWO WAY FSI
Model: 2D Plate
Material: Structural Steel
Element Type: Solid 186
Initial Disturbance and Left Free
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COUPLING
Transient Structural and CFX
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Tip Displacement
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TWO-WAY FSI
1st Time-step
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Results
Damping Motion Shows Transfer of Loads
between Fields
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STATIC AEROELASTIC ANALYSIS
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STATIC AEROELASTIC ANALYSIS
Model Selection : NASA Wind-Tunnel
Experiments on Divergence of Forward
Swept Wing(Aug 1980)
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Model Specification
MODEL 1 MODEL 2
SWEEP -30˚ -15˚
TAPER 1 1
AR 4 4
TRANSITION STRIP NO.46 CARBORANDUM
GRIT
NO 46 CARBORANDUM
GRIT
MODEL MOUNT CANTILEVER CANTILEVER
AOA .1˚ .1˚
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Experimental Results
MODEL 1(-30 Sweep) MODEL 2(-15 Sweep)
DIVERGENCE
SPEED(m/s)
51 73.41
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Ref: Wind-Tunnel Experiments on Divergence of Forward-Swept Wings,
NASA Technical Paper 1685
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MODEL 1 = -30˚
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MODEL 1: -30˚
Model
Transition Strip is not Modelled
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Monitor Point
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Velocity = 45m/s
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Divergence Speed(-30˚ Sweep)
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V= 48 m/s V= 45 m/s
Divergence Speed ≈ 46.5 m/s
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DEFORMATION
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Velocity = 48 m/s
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MODEL 2 = -15˚
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Wingtip Displacement
Velocity = 75 m/s
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Velocity = 80 m/s
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Wingtip Displacement
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Divergence Speed(-15˚ Sweep)
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V= 80 m/s V= 78 m/s
Divergence Speed≈ 79 m/s
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RESULTS
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Divergence Speed
ANSYS
(m/s)
EXPERIMENTAL
(m/s)
Error
MODEL 1 46.5 51 8.8%
MODEL 2 79 73 8.2%
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RESULTS
Divergence Dynamic Pressure
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CONCLUSION
Divergence Results are in Good
Agreement with the Experimental Results
Difference in Results is due to Simplified
Model
Divergence Speed Increase as Wing
Sweep Back Increases
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DYNAMIC AEROELATIC STUDY
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Methodology
Model Selection = AGARD 445.6
Geometric ModellingMode Shape and Modal Frequency
Matching
Flutter Boundary Calculation of AGARD
wing
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AGARD 445.6 WING
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Holes are Drilled to Reduce Stiffness
Number of Holes are Unknown
Modelling Holes Creates Extra Surfaces
that Increase Processing Time
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Problems
Structural Properties are not Well Defined
Modal Matching Requires an Iterative
Process
Dynamic Pressure Matching Requires
Iterative Process
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Model
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Mesh
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Modal Frequency Matching
Density is Tuned to 390 kg/m3 to Match
Modes
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Mode ANSYS EXPERIMENTAL ERROR
1 9.61 9.6 .1%
2 40.098 38.10 5.2%
3 50.4 50.7 .5%
4 96.63 98.5 1.8%
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Mode Shapes
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Mode 1 Mode 2
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Mode Shapes
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Mode 3 Mode 4
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Flutter Analysis
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Flutter Analysis
General Solution Methods• Time Domain Method
• Frequency Domain Method
Flutter Solution is Mostly Found using
Frequency Domain Method• Simple Technique, Quick Solution
ANSYS uses Time-Domain Method• Average Time per Run ≈ 72 hour
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Flutter Analysis
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Setting Desired Mach
Number
Varying Dynamic Pressure
Checking Time
History of Motion
FFT of Time-
History of Motion
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Flutter Analysis
Flutter Analysis is Performed at only one
Mach# due to Unbearably Large Solution
Time
Solution Time for one Flutter Test is >72Hr
Dynamic Pressure is Changed at Constant
Mach Number till Flutter is Achieved
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Result
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Mach = .9
Dynamic Pressure = 4520 Pa
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Flutter Boundary at Mach=.9
(Flutter Dynamic Pressure)
ANSYS
• 4520 Pa
Experimental
• 4500 Pa
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Flutter Frequency
Error in Tip-Displacement Plot due to Data
Corruption
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Flutter Frequency
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Neglecting the First Jump,
Computed Experimental %age Error
Flutter
Frequency(Hz)
17 20.35 16%
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Flutter in ANSYS Workbench
The First time, Flutter is Performed in
ANSYS WB.
Flutter Frequency Can be Improved by
making the Mesh more Fine– Adds Solution Time
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Additional Work
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Two-way FSI (APDL + FLOTRAN)
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Two-way FSI
Multi-field Solver(ANSYS
Workbench)
Physics File-Based Procedure
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Two-way FSI (APDL + Flotran)
Multi-field Solver(ANSYS Workbench) • Allows FSI of only 3D Geometry
• Element Selection is not Allowed
Physics File-Based Procedure(APDL+Flotran)
• Requires Node to Node Matching Mesh of
Structural and Fluid part
• Problematic in 3D
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Two-way FSI (APDL + Flotran)
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Methodology
Modelling Geometry
Element Selection
Defining Morphing Region
Flow Solution
Reading Pressure into a File
Applying Pressure Loads on Structure
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Two-way FSI (APDL + Flotran)
Methodology
Send Deformation to Fluid Physics
Morph The Mesh
Solve Fluid Physics
Read Pressure Loads
Apply Pressure on Structure
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Geometry
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Results
Tip Motion
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Results
Streamlines
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Results
Von-Mises Stress
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1st Time-Step
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Results
Von-Mises Stress
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Last Time-Step
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Conclusion
Significant Changes in Stress if
Deformation is Considered
Accurate Prediction of Lift if Deformation is
Considered
All the Milestones Successfully Achieved
Extra Task of Doing Two-way FSI in APDL
achieved
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References
Wind-Tunnel Experiments on Divergence of Forward-Swept Wings, NASA Technical
Paper 1685
AGARD Standard Aeroelastic Configurations for Dynamic Response. Candidate
Configuration I.-Wing 445.6, NASA TM-100492
Time and Frequency Domain Flutter Solutions for The AGARD 445.6 Wing
by Ryan J. Beaubien, Fred Nitzsche, and Daniel Feszty
Static Aeroelastic Analysis of the Arw-2 Wing Including Correlation with Experiment
By Joseph P. Hepp
(Department of Mechanical Engineering and Material Science Duke University)
AGARD Report 765, Dynamic Aeroelastic Analysis of AGARD 445.6 Wing
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Thank You
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Questions
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