SLIDE 1
Aeroelastic Workshop:
The Validation of Aeroelastic Simulations using STAR-CCM+ coupled to Abaqus
SLIDE 2 Validate the accuracy of STAR-CCM+ coupled to Abaqus for aeroelastic applications The HIRENASD project was chosen as good source of aeroelastic measurement data Performed simulations and analyzed responses:
- Aeroelastic equilibrium (fluid-structure coupled)
- Modal analysis (structure only, vacuum)
- Impulsive loading (fluid-structure coupled)
- Prescribed 2nd bending mode motion (fluid only)
- 1st bending mode excitation via prescribed moment applied to structure
(fluid-structure coupled)
Credit: S. Zhelezov, A. Mueller (CD-adapco)
The Aeroelastic Workshop
SLIDE 3
High Reynolds Number Aerostructural Dynamics (HIRENASD) Funded by the German Research Foundation (DFG) Experiments on an elastic wing model at transonic flight conditions in the European Transonic Windtunnel in Cologne To provide free data on dynamic aeroelastic experiments at conditions typical for large transport aircrafts in cruise flight
The HIRENASD Project
SLIDE 4 The HIRENASD Project
.cgns file .bdf file
cgns: CFD General Notation System bdf: Nastran
Minor mismatch of meshes
project webpage (trailing edge) nodes: 20k cells: 5M .bdf .cgns Mismatch was corrected to allow for proper mapping
SLIDE 5
The Models
Abaqus 53k nodes STAR-CCM+ 8.5M cells
SLIDE 6
Aeroelastic Equilibrium Configuration (AEC)
The AEC AEC is a stable configuration the wing adopts due to the steady aero loads. External and internal forces are in balance (equilibrium).
SLIDE 7
Aeroelastic Equilibrium Configuration (AEC)
CL: Coefficient of Lift CD: Coefficient of Drag AoA: Angle of Attack
Comparison of STAR-CCM+ to experimental results and SOFIA 1) 2)
q/E = 0.48E-06, M = 0.8, Re = 23.5E06
SLIDE 8
Aeroelastic Equilibrium Configuration (AEC)
Comparison of STAR-CCM+ to experimental results and SOFIA 2)
q/E = 0.48E-06, M = 0.8, Re = 23.5E06
SLIDE 9
Aeroelastic Equilibrium Configuration (AEC)
Comparison of STAR-CCM+ to experimental results and FUN3D 3)
Cp: Coefficient of pressure
STAR-CCM+ FUN3D
q/E = 0.48E-06, M = 0.8, Re = 23.5E06, alpha = 2°, station 7, eta = 0.95
SLIDE 10
Experiment 4) Reported value SOFIA model 5) Abaqus model Frequency: 25.75 Hz 26.46 Hz 26.55 Hz Error: 3.15 % 3.11 %
Modal Analysis
Modal analysis of structure only (corresponds to vacuum) 1st bending mode 2nd bending mode
SLIDE 11
Response to impulsive loading
Coupled Fluid Structure analysis
Experiment 6) Reported value SOFIA model 5) STAR-CCM+ Abaqus Co Sim. Frequency: 29.10 Hz 29.55 Hz 29.54 Hz Error: 1.55 % 1.51 %
STAR-CCM+ SOFIA 5) q/E = 0.48E-06, M = 0.8, Re = 23.5E06, AoA = -1.34°, Nitrogen
SLIDE 12
Prescribed 2nd bending mode motion
Experiments were performed by exciting the 2nd bending mode at its resonant frequency Abaqus predicted 2nd bending mode scaled to match measured wing tip amplitude about the predicted AEC configuration
SLIDE 13
Prescribed 2nd bending mode motion
Fourier transform of Cp on upper surface at position 7 Experiment 7) and results of STAR-CCM+ simulation (fluid only)
SLIDE 14
Prescribed 2nd beding mode motion
Fourier transform of Cp on lower surface at position 4 Experiment 7) and results of STAR-CCM+ simulation (fluid only)
SLIDE 15 STAR-CCM+ Experiment SOFIA Experiment
- cp´ / acc15/1
- cp´ / acc15/1
1st bending mode excitation
Experiments were performed by exciting the 1st bending mode at its resonant frequency 2-way coupled simulation with 1st bending mode moment excitation in structural model
change in cp relative to tip acceleration -cp´/acc15/1 2) 8)
Experiment 2.23E-04 STAR-CCM+ 1.79E-04 Error 19.73% Experiment 2.23E-04 SOFIA 1.99E-04 Error 10.76%
q/E = 0.48E-06, M = 0.8, Re = 23.5E06, AoA = -1.34°, Nitrogen
SLIDE 16 1)
- J. Ballmann et al. Aero-structural Dynamics Experiments at High Reynolds Numbers. Springer-
Verlag Berlin Heidelberg 2010. 2) Reimer, L., Boucke, A., Ballmann, J., and Behr, M. “Computational Analysis of High Reynolds Number Aero-Structural Dynamics (HIRENASD) Experiments,” IFASD-2009-130, International Forum on Aeroelasticity and Structural Dynamics, Seattle, WA, June 21-25, 2009 3) J.Heeg, J.Florance, P.Chwalowski, B. Perry, C.Wieseman. Information Package: Workshop on Aeroelastic Prediction. Aeroelasticity Branch, NASA Hampton, Virginia. October 2010 4)
- H. Korsch, A. Dafnis, H. G. Reimerdes, C. Braun, J. Ballmann, “Dynamic Qualification of the
HIRENASD elastic wing model”, Annual Meeting of the German Aerospace Association (DGLR), Paper DGLR-2006-045, Braunschweig, 2006. 5) Reimer, L., Braun, C., Chen, B.-H., Ballmann, J.: Computational Aeroelastic Design and Analysis
- f the HIRENASD Wind Tunnel Wing Model and Tests. In proc. of the International Forum on
Aeroelasticity and Structural Dynamics (IFASD) 2007, Paper IF-077, Stockholm, Sweden, 2007. 6) J.Ballmann et al. Experimental Analysis of High Reynolds Number Aero-Structural Dynamics in ETW, AIAA 2008-841, Presented at the 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 7-10, 2008. 7) Email correspondence with Jennifer Heeg at NASA on 16th April 2012 regarding updated data for Experiment #271 of the HIRENASD project. 8)
- J. Ballmann. Aeroelastische Windkanalversuche mit flexiblen Tragfluegeln bei realen
Reynoldszahlen (HIRENASD - ASDMAD). Wissenschaftstag DLR Institut FA, Braunschweig, 30.9.2010.
References
SLIDE 17 The accuracy of STAR-CCM+ coupled to Abaqus for aeroelastic applications was successfully validated Excellent agreement to the reported experimental data was
- btained for all studied cases:
- Aeroelastic equilibrium
- Modal analysis
- Response to impulsive loading
- Prescribed 2nd bending mode motion
- 1st bending mode excitation via prescribed moment applied to structure
It was shown that the accuracy of the results obtained with STAR-CCM+ coupled to Abaqus are comparable to specialized aeroelastic codes
Summary
