NASA Icing Update – Oct 2024 Presentation for the SAE AC-9C Technical Committee Meeting Oct 21, 2024│Ottawa, ON, CANADA
National Aeronautics and Space Administration
NASA Icing Update – Oct 2024
Presentation for the SAE AC-9C Technical Committee Meeting Oct 21 , 2024│Ottawa, ON, CANADA Contributors Andy Broeren, Ru-Ching Chen, Thomas Ozoroski, Chris Porter, Paul Von Hardenberg Presented by: Judy Van Zante NASA Glenn Research Center, Cleveland, Ohio, USA www.nasa.gov
NASA’s Mission in Icing
National Aeronautics and Space Administration NASA’s Mission in Icing NASA maintains world-class facilities for icing research and is developing tools and methods for simulating and evaluating the growth of ice on current and future aircraft surfaces or inside engines and the effect(s) that ice may have on the behavior of aircraft in flight.
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Outline
National Aeronautics and Space Administration
Outline
1. Transonic Truss-Braced Wing Icing (Broeren) 2. High-Lift Common Research Model Icing (Broeren) 3. Adaptive Icing Tunnel (Chen) 4. Advanced Air Mobility Icing 5. GlennICE Update www.nasa.gov
Transonic Truss-Braced Wing Icing
National Aeronautics and Space Administration
Transonic Truss-Braced Wing Icing
Background • NASA is collaborating with Boeing as a part of the Subsonic Ultra-Green Aircraft Research (SUGAR).
• A portion of this collaboration is dedicated to exploring the impacts of icing on the TTBW configuration.
Icing Research Tasks • IRT testing of TTBW components: (1) wing-truss junction region and (2) wing section with variable camber Krueger flap.
• Icing simulations with GlennICE and LEWICE3D: full aircraft in flight and wing sections in IRT.
• Iced aerodynamic testing with artificial ice shapes: semispan model at QinetiQ 5m wind tunnel.
• Iced aerodynamics CFD simulations: exploring wall -modeled LES methods • Icephobic materials development: emphasis on durability in addition to low ice adhesion www.nasa.gov Project Sponsor: AATT
Transonic Truss-Braced Wing Icing
National Aeronautics and Space Administration
Transonic Truss-Braced Wing Icing
IRT Testing of Wing-Truss Junction Model • A full-scale section of the wing with the strut and pylon was extracted from the airplane geometry.
• The resulting test article is large relative to the test section and maintains the full 3D features of the airplane.
– No truncated design – No extruded wing section www.nasa.gov Project Sponsor: AATT
Transonic Truss-Braced Wing Icing
National Aeronautics and Space Administration
Transonic Truss-Braced Wing Icing
IRT Testing of Wing-Truss Junction Model • Model designed such that it can be tested with and without the strut/pylon.
• No flap—will match attachment line location with angle of attack adjustments.
• IRT test campaign planned for Fall 2024.
• Test objectives: – Explore effect of ceiling gap on surface pressures and flow separation – Explore potential critical ice shape scenarios – Validation data for GlennICE and LEWICE3D www.nasa.gov Project Sponsor: AATT
High-Lift Common Research Model Icing
National Aeronautics and Space Administration
High-Lift Common Research Model Icing
Background • The HL-CRM was developed for a series of AIAA workshops on CFD predictions (HLPW).
• The HL-CRM was first utilized in HLPW-3 conducted in June 2017.
• HLPW-5 was conducted in July 2024.
• Currently, there are at least nine different wind tunnel models based upon the HL-CRM geometry.
• Numerous wind-tunnel tests have been performed over a large range of Reynolds and Mach numbers.
Icing Effects • The effects of ice on aerodynamic performance were introduced into the HL-CRM ecosystem in 2019.
• Goal is to benchmark CFD capability for iced high -lift configuration aerodynamics.
www.nasa.gov Project Sponsor: TTT
High-Lift Common Research Model Icing
National Aeronautics and Space Administration
High-Lift Common Research Model Icing
NASA-Boeing Collaboration • Developed artificial ice shapes using LEWICE3D for HL-CRM icing scenario.
• In Spring 2022, performed risk-reduction testing for adhering artificial ice shapes to a wind-tunnel model in a cryogenic environment • In Spring 2024, performed artificial ice shape aerodynamic test on 5.2% semispan model of HL- CRM in NASA National Transonic Facility (NTF).
• Planned NTF test campaigns with 2.7% scale full- span and semispan models up to Re up to 16×10 at M = 0.26 www.nasa.gov Project Sponsor: TTT
High-Lift Common Research Model Icing
National Aeronautics and Space Administration
High-Lift Common Research Model Icing
NASA-ONERA-NRC Collaboration “SUNSET 3” • NASA, ONERA and NRC are collaborating on high-lift system icing.
• ONERA will perform aerodynamic testing at F1 pressurized wind-tunnel using their 1/19.5 scale full span HL-CRM.
– All groups will generate ice shapes with in-house codes (e.g., GlennICE , IGLOO3D, NRC Morphogenic, LEWICE3D).
– NASA will fabricate artificial ice shapes for F1 test campaign.
• NRC will perform icing tests on small-scale, high-lift airfoil model in the Altitude Icing Wind Tunnel (AIWT).
– Initial icing test campaign planned for Fall 2024.
• All groups plan to perform additional CFD simulations for comparison to iced HL -CRM aerodynamic data and icing simulations for comparison to ice accretion test data.
www.nasa.gov Project Sponsor: TTT
High-Lift Common Research Model Icing
National Aeronautics and Space Administration
High-Lift Common Research Model Icing
High-Lift Prediction Workshop with Ice Effects • Iced HL- CRM aerodynamic data collected in this effort is being directed toward a CFD prediction workshop that includes effect of ice on airplane performance including C .
L,max • The intent is to engage the current CFD community working in the HLPW series in the unique aspects and challenges of iced aerodynamics.
• The timing and location of HLPW with ice effects is still being planned. Communication and coordination with the icing community (e.g. IPW committee) is being maintained to avoid obvious conflicts with major events in the icing community.
www.nasa.gov Project Sponsor: TTT
Adaptive Icing Tunnel (AIT)
National Aeronautics and Space Administration Adaptive Icing Tunnel (AIT) Description • Laboratory scale icing wind tunnel • Closed loop, vertical • Test section 1 x 1 ft (0.3 x 0.3 m) Features 1. Fan 2. Heat Exchanger 3. Spray Bars 4. Test Section 5. Walk-in Freezer www.nasa.gov Project Sponsor: AATT, AETC, RVLT, TTT
Adaptive Icing Tunnel
National Aeronautics and Space Administration
Adaptive Icing Tunnel
Capabilities • Airspeeds up to ~210 knots (~110 m/s) • Temperatures as cold as -20°C • Walk-in freezer around test section • Supercooled Liquid and Ice Crystal Expect to start testing Jan 2025 • Calibration • Ice Adhesion Testing • Probe development Walk-in Freezer installed 1. Fan 3. Spraybars Aug 2024 2. Heat Exch. 4. Test Section www.nasa.gov Project Sponsors: AATT, AETC, RVLT, TTT
Advanced Air Mobility (AAM) Icing
National Aeronautics and Space Administration
Advanced Air Mobility (AAM) Icing
PROBLEM While icing engineering tools and methods for means of compliance are
fairly mature for existing legacy aircraft, there are no accepted icing engineering tools specifically developed and rigorously tested for AAM class vehicles.
OBJECTIVE Develop experimental and computational icing simulation capabilities for eVTOL vehicles.
NASA Tiltwing Concept Vehicle APPROACH (cruise configuration) • Acquire experimental ice shapes on non-proprietary propeller/rotor geometries for code validation and development.
• Establish best practices and scaling methodologies for conducting icing tests on rotating geometries.
• Acquire experimental shedding data to support development of ice shedding prediction capabilities.
ACCOMPLISHMENTS • Successfully completed two test entries of a generic eVTOL propeller in the Icing Research Tunnel in 2023 and 2024.
• Acquired ice shapes, propeller performance degradation, and high -speed images of shedding events.
AAM Propeller Test Stand Installed in Icing Research Tunnel (IRT) www.nasa.gov Project Sponsor: RVLT, AATT
NASA Icing Tools - GlennICE
National Aeronautics and Space Administration
NASA Icing Tools - GlennICE
Acts as a CFD post processor [1] GlennICE Lagrangian droplet tracking with adaptive refinement External Icing Fully 3D icing simulation and particle tracking tool Rotational Icing Predicts water impingement & resulting ice growth on arbitrary Ice Crystal Icing aircraft surfaces Fully parallelized trajectory scheme built for HPCs As of 2018,GlennICE is the foundational code through which NASA will develop and evaluate physical models associated with ice accretion ARIES-I Transonic Truss Braced Wing Common Research Model - High Lift www.nasa.gov [1] “GlennICE Manual 4.1.0.” NASA Glenn Research Center , NASA-TM-20240002191, https://ntrs.nasa.gov/citations/20240002191 Project Sponsors: AATT, RVLT, TTT
GlennICE Fan Icing
National Aeronautics and Space Administration
GlennICE Fan Icing
FY24-FY26 TTT and Engine Fan Icing Work Areas: AATT/PT • 3D rotational icing simulation Coordination • Rotating Reference Frame, Mixing Planes, Water Runback, and Periodic Boundary Conditions • Ice shedding simulation • Model onset time and mass of shed ice • Defining requirements for engine fan icing test rig • Actively meeting with industry stakeholders • The GlennICE Software is utilized by various organizations: – AATT/AT – Transonic Truss Braced Wing – AATT/PT – Efficient Quiet Integrated Propulsor – AETC – Icing Research Tunnel CFD Characterization GlennICE development coordination to support AATT/PT EQUIP Technical Challenge.
External Customers www.nasa.gov Project Sponsors: AATT, TTT
Summary
National Aeronautics and Space Administration
Summary
Icing research in this briefing: • TTBW • High-Lift CRM • AIT • AAM Icing • GlennICE Update • 2024 AIAA Aviation Papers www.nasa.gov
Thank You!
National Aeronautics and Space Administration
Thank You!
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