Document
www.nasa.gov June 22-25, 2015
Andy Broeren
Prague, Czech Republic
and Aerodynamics
NASA Glenn Research Center
Summary of Research and Current Status
NASA/FAA/ONERA Swept-Wing Icing
SAE Icing Conference National Aeronautics and Space Administration www.nasa.gov :
Acknowledgements
NASA FAA ONERA Boeing University of Illinois University of Virginia University of Washington
Sponsor Organizations • • • Supporting Organizations: • • • •
National Aeronautics and Space Administration www.nasa.gov
Outline
Introduction Goals and Objectives Research Roadmap Description of Research Phases Summary Advertisement References
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Introduction
Development and use of 3D icing simulation tools. Lack of ice accretion and aerodynamic data for large- scale, swept wing geometries. Aerodynamic understanding important for evaluating efficacy of 3D icing simulation tools. Multi-phase research effort.
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National Aeronautics and Space Administration www.nasa.gov
Goal and Objectives
Improve experimental and computational simulation. Generate a database of 3D ice-accretion geometry. Generate a database of iced-wing aerodynamic effects. Quantify ice-shape geometric fidelity requirements.
Overall Goal • Objectives • • •
National Aeronautics and Space Administration www.nasa.gov Completed Future Work Current Work Phase VI: High-Reynolds Number Validation Testing Phase V: Low-Reynolds Number Aerodynamic Testing Phase IV: High-Reynolds Number Aerodynamic Testing Phase III: Ice Accretion Testing
Research Roadmap
Phase VII: 3-D Ice Accretion and Flowfield Computational Simulation Measurement Methods Development Phase II: Ice Accretion and Aerodynamic Phase I: 3-D Ice Accretion Classification National Aeronautics and Space Administration www.nasa.gov
Phase I: Ice-Shape Classification
Roughness Streamwise ice Horn ice Spanwise-ridge ice
Define ice shapes based on their aerodynamic characteristics. • • • •
National Aeronautics and Space Administration www.nasa.gov Common Research Model selected as the baseline, full-scale, reference geometry for the swept-wing configuration. Applied and validated existing 3D laser scanning methods to measure highly 3D ice accretion. Applied existing 3D wake survey methods to iced swept wings.
Phase II: Measurement Methods Development
• • • National Aeronautics and Space Administration www.nasa.gov
Common Research Model (CRM)
Commercial transport class configuration. Contemporary transonic supercritical wing design. Publically available and otherwise unrestricted for world-wide distribution. A 65% scale CRM was selected as the full-scale, reference swept-wing geometry for this research. CRM65 size airplane is comparable to Boeing 757.
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National Aeronautics and Space Administration www.nasa.gov 83% semispan Outboard model 64% semispan Midspan model 20% semispan Inboard model
Phase III: Ice Accretion Testing
oral presentation by Emmanuel Radenac SAE paper 2015-01-2122 by Eric Loth
− −
Three spanwise stations selected for IRT testing. Required hybrid model design—see oral presentation by Gustavo Fujiwara. Related presentations: A two-week IRT test campaign was completed for each model.
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National Aeronautics and Space Administration www.nasa.gov 2.0 1.5 2.25 Factor Model Scale 6.3 6.2 13.5 Chord Length (ft) Streamwise
Phase III: Ice Accretion Testing
Pressure instrumentation Icing − − Full-scale leading edge, truncated afterbody. Streamwise pressure taps located at three spanwise stations. Single-element, slotted flap with anti- icing heater. Two removable leading edges Model Section Inboard Midspan Outboard
Models Description • • • •
National Aeronautics and Space Administration 45 45 min.
www.nasa.gov Exp. Time 0.51 0.36 LWC g/m 0.17 to 0.55 m 20 20 20 μ MVD -13.0 deg. C Static Temp -25.0 to -6.0 -10.0 to -3.0 -4.1 deg. C -6.0 to 1.1 Total Temp -18.4 to 1.1 230 220 260 TAS Knots 3.3 4.4 2.1
Phase III: Ice Accretion Testing
AoA deg.
Conditions were scaled to IRT test speed (130 knots for most cases). See oral presentation by Paul Tsao.
− − Generate range of ice accretion (Phase I). Hold and descent for CRM65 airplane in App. C. Large range of temperatures, limited variations in MVD and LWC. Large model size limited maximum speed in IRT.
33 41 52 Case
Icing Test Matrix Development • • • • Baseline Flight Reference Conditions
National Aeronautics and Space Administration 29 29 29 min.
www.nasa.gov Exp. Time 1.0 1.0 1.0 g/m LWC Total Temp = -23.8 deg. C m 25 25 25 μ MVD -6.0 -11.0 -25.0 deg. C Static Temp Total Temp = -8.7 deg. C -3.8 -8.7 -23.8 deg. C Total Temp 130 130 130 TAS Knots 3.7 3.7 3.7
Phase III: Ice Accretion Testing
AoA deg.
Run TG2410 TG2402 TG2415 Total Temp = -3.8 deg. C Inboard Model—Effect of Temperature National Aeronautics and Space Administration 29 29 29 min.
www.nasa.gov Exp. Time 1.0 1.0 1.0 g/m LWC Outboard m 25 25 25 μ MVD -8.5 -8.5 -8.5 deg. C Static Temp Midspan -6.3 -6.3 -6.3 deg. C Total Temp 130 130 130 TAS Knots 3.7 3.7 3.7
Phase III: Ice Accretion Testing
AoA deg.
Inboard Run TI2461 TG2411 TH2450 Identical Condition Run on Each Model National Aeronautics and Space Administration min.
www.nasa.gov Exp. Time 1.0 g/m LWC m μ MVD -8.5 deg. C Static Temp -6.3 deg. C Total Temp TAS Knots 3.7
Phase III: Ice Accretion Testing
AoA deg.
Run TG2450 Time lapse video—Midspan Model National Aeronautics and Space Administration www.nasa.gov oral
= 12×10
Re
by Sam Lee.
= 0.3.
M
Build and test 13.3% scale model of the CRM65 in ONERA F1 pressurized wind tunnel. Range of Reynolds and Mach numbers up to and Design and build full-span artificial ice shapes from the IRT tests of the 20%, 64% and 83% semispan stations of the CRM65 wing—see presentation Vary the geometric fidelity and quantify aerodynamics.
Phase IV: High-Re Aerodynamic Testing
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National Aeronautics and Space Administration www.nasa.gov
and
= 2.4×10
Re
= 0.27.
August 2014—see oral presentation by Brian Woodard. Wichita State University 7 ft. x 10 ft. size wind tunnel.
Initial test campaign completed in 8.9% scale CRM65 was built for the Aerodynamic performance and 3D wake surveys up to M Scale models of the artificial ice shapes used in the ONERA F1 tests. Quantify the differences between low and high-Re results. Investigate sensitivity to ice features.
Phase V: Low-Re Aerodynamic Testing
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National Aeronautics and Space Administration www.nasa.gov
=
Re
= 0.3.
M
and
Identify critical ice shape configurations from Phase V. Build and test these configurations in ONERA F1 pressurized wind tunnel. Range of Reynolds and Mach numbers up to 12×10 Quantify the differences in aerodynamic performance and key flowfield features between the low and high- Reynolds number tests.
Phase VI: High-Re Validation Testing
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National Aeronautics and Space Administration www.nasa.gov
Phase VII: Computational Simulation
Identify critical elements for accurate ice- shape predictions and iced swept wing aerodynamics.
NASA will investigate methods for smoothing and gridding of ice-accretion geometry from the 3D scan data of the IRT ice accretion leading to computational flow simulations. ONERA will investigate the use of the “Immersed Boundary Conditions” (IBC) method in order to take the exact ice shape into account without having to mesh it explicitly. Conducted in parallel with the other tasks throughout the project.
• • • • National Aeronautics and Space Administration www.nasa.gov
Summary
The anticipated research products are: Database of swept-wing ice accretion geometry Database of high-Reynolds number aerodynamic data for swept- wing ice accretion. An understanding of the geometric fidelity required for accurate aerodynamic simulation of swept-wing ice accretion. Hybrid-model design methods for conducting icing-tunnel tests of large-scale swept wings. A validated low-cost, low-Reynolds number test capability for evaluation of performance characteristics and aerodynamics of iced-swept-wing geometries. Improved methods for quantifying ice accretion geometry and developing high-fidelity artificial ice shapes.
• • • • • • NASA, FAA and ONERA are sponsoring a research effort dedicated to improving computational and experimental simulation methods for swept-wing icing.
National Aeronautics and Space Administration www.nasa.gov Andy Brian Broeren Gustavo Fujiwara Eric Loth Sam Lee Woodard Radenac Paul Tsao Emmanuel
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NASA/FAA/ONERA Swept-Wing Icing and Aerodynamics: Summary of Research and Current Status Design of Wind Tunnel Models for Full-Scale Swept-Wing Ice Accretion Detached Eddy Simulation on a Swept Hybrid Model in the IRT Method to Generate Full-Span Ice Shape on Swept Wing Using Icing Tunnel Data Initial Low-Reynolds Number Iced Aerodynamic Performance for CRM Wing 3D Modeling of Ice Accretion with Application to Swept Wing Test-Cases Velocity Effect on Swept-Wing Ice Accretion for Scaling Consideration NASA/FAA/ONERA Swept-wing Icing & Aerodynamics—Part 1 of 2 NASA/FAA/ONERA Swept-wing Icing & Aerodynamics—Part 2 of 2 Oral Only Oral Only Oral Only Oral Only Oral Only Oral Only SAE Paper 2015-01-2122 Stay tuned in the next two sessions: National Aeronautics and Space Administration www.nasa.gov
References 2012-2013
Diebold, J.M., Monastero, M.C., and Bragg, M.B., “Aerodynamics of a Swept-Wing with Ice Accretion at Low Reynolds Number,” AIAA Paper 2012-2795, June 2012. Lee, S., Broeren, A.P., Addy, H.E., Jr., Sills, R., and Pifer, E.M., “Development of 3-D Ice Accretion Measurement Method,” AIAA Paper 2012-2938, June 2012, also NASA TM—2012-217702, Sept. 2012. Diebold, J.M., “Aerodynamics of a Swept Wing with Leading-Edge Ice at Low-Reynolds Number,” M.S. Thesis, Dept. of Aerospace Eng., Univ. of Illinois, Urbana, IL, Aug. 2012. Mortonson, A.J., “Use of Hybrid Airfoil Design in Icing Wind Tunnel Tests of Large Scale Swept Wings,” M.S. Thesis, Dept. of Aerospace Eng., Univ. of Illinois, Urbana, IL, 2011. Diebold, J.M., and Bragg, M.B., “Study of a Swept-Wing with Leading-Edge Ice Using a Wake Survey Technique,” AIAA Paper 2013-0245, Jan. 2013. Broeren, A.P., Diebold, J.M., and Bragg, M.B., “Aerodynamic Classification of Swept-Wing Ice Accretion,” NASA TM 2013-216381, DOT/FAA/TC-13/21, May 2013. Broeren, A.P., Potapczuk, M.G., Riley, J.T., Villiedieu, P., Moens, F., Bragg, M.B., “Swept-Wing Ice Accretion Characterization and Aerodynamics,” AIAA Paper 2013-2824, June 2013, also NASA TM—2013-216555, Sept. 2013. Broeren, A.P., Diebold, J.M., and Bragg, M.B., “Aerodynamic Classification of Swept-Wing Ice Accretion,” AIAA Paper 2013-2825, June 2013. Fujiwara, G.E.C., Woodard, B.S., Wiberg, B.D., Mortonson, A.J., Bragg, M.B., “A Hybrid Airfoil Design Method for Icing Wind Tunnel Tests,” AIAA Paper 2013-2826, June 2013. Wiberg, B.D., “Large-Scale, Swept-Wing Ice Accretion Modeling in the NASA Glenn Icing Research Tunnel Using LEWICE3D, M.S. Thesis, Dept. of Aerospace Eng., Univ. of Illinois, Urbana, IL, 2013. Monastero, M.C., “Validation of 3-D Ice Accretion Documentation and Replication Method Including Pressure- Sensitive Paint,” M.S. Thesis, Dept. of Aerospace Eng., Univ. of Illinois, Urbana, IL, 2013.
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National Aeronautics and Space Administration www.nasa.gov RF 1/21372 DMEA/DAAP/DSNA, Mars 2014. RF 1/22549 DMEA/DAAP/DSNA, Avil 2015.
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References 2014-2015
Moens, F., Costes, M., Terracol, M., Radenac, E., Trontin, P., and Villedieu, P., “Rapport D’advancement du Projet SUNSET 2 en 2013,” ONERA Rapport Final N Lee, S., Broeren, A.P., Kreeger, R.E., Potapczuk, M.G., and Utt, L., “Implementation and Validation of 3-D Ice Accretion Measurement Methodology,” AIAA Paper 2014-2613, June 2014. Broeren, A.P., Lee, S.L., Addy, H.E., Jr., and Monastero, M.C., “Validation of 3-D Ice Accretion Measurement Methodology for Experimental Aerodynamic Simulation,” AIAA Paper 2014-2614, June 2014. Monastero, M.C., and Bragg, M.B., “Validation of 3-D Ice Accretion Measurement Methodology Using Pressure- Sensitive Paint,” AIAA Paper 2014-2615, June 2014. Fujiwara, G.E.C., Wiberg, B.D., Woodard, B.S., and Bragg, M.B., “3D Swept Hybrid Wing Design Methods for Icing Wind Tunnel Tests,” AIAA Paper 2104-2616, June 2014. Wiberg, B.D., Fujiwara, G.E.C., Woodard, B.S., and Bragg, M.B., “Large-Scale, Swept-Wing Icing Simulations in the NASA Glenn Icing Research Tunnel Using LEWICE3D,” AIAA Paper 2014-2617, June 2014. Jun, G., Oliden, D., Potapczuk, M.G., and Tsao, J-C., “Computational Aerodynamic Analysis of Three-Dimensional Ice Shapes on a NACA 23012 Airfoil, AIAA Paper 2104-2202, June 2014. Fujiwara, G.E.C., “Design of 3D Swept Wing Hybrid Models for Icing Wind Tunnel Tests,” M.S. Thesis, Dept. of Aerospace Eng., Univ. of Illinois, Urbana, IL, 2014. Diebold, J.M., Woodard, B.S., Monastero, M.C., and Bragg, M.B., “Experimental Study of Splitter Plates for Use with Semispan Wing Models,” AIAA Paper 2015-1227, Jan. 2015. Costes, M., Terracol, M., Michel, B., Radenac, E., Gaible, H., and Bezard, H., “Rapport D’advancement du Projet SUNSET 2 en 2014,” ONERA Rapport Final N 12. 13. 14. 15. 16. 17. 18. 19. 20. 21.
National Aeronautics and Space Administration www.nasa.gov
Baseline Swept-Wing Model Selection
Common Research Model (CRM). Commercial transport class configuration. Contemporary transonic supercritical wing design. Publically available and otherwise unrestricted for world-wide distribution.
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Reference: Vassberg, J.C., DeHann, M.A., Rivers, S.M., and Wahls, R.A., “Development of a Common Research Model for Applied CFD Validation Studies,” AIAA Paper 2008-6919, Aug. 2008.
National Aeronautics and Space Administration www.nasa.gov A 65% scale CRM was selected as the full-scale, reference swept-wing geometry for this research.
Baseline Swept-Wing Model Selection
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National Aeronautics and Space Administration www.nasa.gov
3D Ice Accretion Measurement
Requirement for ice accretion database and for artificial ice shapes used in aerodynamic testing. Commercial, laser-based scanning system adapted for ice accretion measurement. Research and validation efforts have been completed.
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National Aeronautics and Space Administration www.nasa.gov 3D wake survey method applied to ice swept wing. Understand origin of ice-wing performance degradation. Development and validation of computational simulation tools.
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3D Aerodynamic Measurement Methods
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