AI-Enhanced Digital Twin Framework for UAS Component Reliability in Support of In-Time Aviation Safety Management Systems (IASMS)

AI-Enhanced Digital Twin Framework for UAS Component Reliability in Support of In-Time Aviation Safety Management Systems (IASMS) is sponsored by National Aeronautics and Space Administration (NASA). This opportunity supports mission-aligned projects and measurable outcomes.

NASA SBIR 2025-I Solicitation Proposal Number: A1. 02-1004 Subtopic Title: Quiet Performance - Airframe Noise Proposal Title: Accurate Airframe Noise Predictions Using Large Eddy Simulations Firm: Volcano Platforms Inc Address: 3240 Hillview Ave, Palo Alto, CA, 94304-1201 E-mail: manlong@volcanoplatforms. com Address: 3240 Hillview Ave, Palo Alto, CA, 94304-1201 E-mail: cetin@volcanoplatforms.

com Address: 14440 Debell Rd, Los Altos Hills, CA, 94022-2061 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 4 Technical Abstract (Limit 2000 characters): Airframe noise generated by the undercarriage (landing gear, cavities) and high-lift devices is by far the most dominant source of noise during approach conditions and has been known to cause adverse health effects in communities residing near airports.

There is a desperate need for computational tools that can rapidly and accurately predict this noise in order to integrate acoustic analysis in the design design process and to meet the regulatory goals around noise reduction.

The current industry standard appears to be a single Lattice Boltzmann hybrid RANS/LES solver; the work proposed in this Phase-I research is intended to remedy this by mitigating several known limitations in the current state-of-the-art.

Volcano ScaLES, an immersed boundary wall-modeled Large Eddy Simulation (WMLES) will be utilized to demonstrate accurate broadband noise predictions on a variety of test cases such as the PDCC-NLG landing gear model, the 30p30n multi-element airfoil and a the 10% scaled high-lift common research model in landing configuration.

We intend to demonstrate that these cases can be completed with overnight turnaround (<16 hours of walltime) using single server/node resources with up to 8 general purpose computing GPUs (such as the Nvidia L40S).

Furthermore, highly automated and rapid mesh generation capable of representing un-simplified complex geometries will be utilized along with entirely in-situ post-processing for farfield acoustics propagation and flow visualization.

Beyond the 3 demonstration problems, additional code enhancements targeting the Ffowcs Williams-Hawkings (FHW) formulation to address the method's well-known drawbacks (such as need for quadrupole corrections) will be also be considered in Phase-I.

If successfully achieved, the goals outlined in the work would represent a major advancement computational predictions of airframe noise, and we anticipate significant interest from both airframe developers and government agencies. Proposal Number: A1.

02-1009 Subtopic Title: Quiet Performance - Airframe Noise Proposal Title: Machine Learning-Augmented Far-Field Noise Prediction for Distributed Electric Propulsion Aircraft Address: 107 Technology Pkwy, Peachtree Corners, GA, 30092-2909 # Principal Investigator Name: Nadin Auda E-mail: nauda@runeaero. tech Address: 3455 PEACHTREE RD NE STE 500, ATLANTA, GA, 30326-3236 E-mail: nauda@runeaero.

tech Address: 3455 PEACHTREE RD NE STE 500, ATLANTA, GA, 30326-3236 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 4 Technical Abstract (Limit 2000 characters): The growing adoption of Distributed Electric Propulsion (DEP) aircraft presents new challenges in aeroacoustic modeling, as multi-propeller interactions, airframe effects, and noise certification requirements become critical barriers to large-scale deployment.

Current low-fidelity noise models fail to capture complex noise sources, while high-fidelity CFD-based simulations are computationally prohibitive for rapid design iteration. To address this, we propose a machine learning-driven surrogate modeling framework that enables real-time, high-accuracy noise prediction for DEP aircraft.

This framework integrates Graph Neural Networks (GNNs) and Fourier Neural Operators (FNOs) to predict full flow-fields and far-field noise signatures, rather than relying solely on empirical regression of noise metrics. Compared to traditional scale-resolving CFD, this approach achieves 1,000x faster computations while maintaining high accuracy (5% MSE with a few hundred simulations).

By leveraging multi-fidelity aeroacoustic data sources (FW-H, VPM, CFD) and embedding physics constraints, the model can generalize across various DEP configurations, enabling faster aircraft design, optimization, and certification.

Phase I funding will be used to develop and validate the FNO-GNN prediction methodology, starting with single-propeller and wing interactions before expanding to multi-propeller DEP configurations in Phase II.

The technology targets NASA aeronautics programs, OEMs (Airbus, Boeing, Joby, Archer, Lilium), defense contractors (Lockheed Martin, Northrop Grumman), and regulatory agencies (FAA, ICAO, EASA), supporting urban air mobility (UAM), hybrid-electric regional aircraft, and UAV applications.

By accelerating DEP aircraft noise prediction and mitigation, this innovation directly supports NASA’s Sustainable Aviation and Advanced Air Mobility (AAM) initiatives, providing a scalable, high-impact solution for future electric aviation. Duration: 6Proposal Details Proposal Number: A1.

03-1009 Subtopic Title: Propulsion Efficiency - Propulsion Materials and Structures Proposal Title: Enabling Material Design within System-Level Optimization via Machine Learning Firm: Collier Research and Development Corporation Address: 760 Pilot House Dr, Newport News, VA, 23606-2068 E-mail: August. Noevere@CollierAerospace. com Address: 760 Pilot House Dr, Newport News, VA, 23606-2068 E-mail: megan.

cameron@collieraerospace. com Address: 760 Pilot House Drive, Newport News, VA, 23606-2068 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 6 Technical Abstract (Limit 2000 characters): The focus of the proposed work is on new tools, primarily enabled with machine learning, to establish a stronger link between composite material selection, and design of materials, and vehicle-level design.

This will be especially beneficial where extensive material test data is not readily available, such as novel materials for applications with extreme environments in propulsion structures. The effort outlined in this proposal starts with the structural analyst/designer viewpoint and would use machine learning to develop tools to build a bridge to materials scientists/engineers.

The HyperX software, a tool for performing structural analysis and optimization at the vehicle/system level, will be used as the foundation of this approach. Structural optimization at a vehicle/system level can require between 1,000 to 100,000 candidate evaluations per component, repeated over 100s or 1,000s of components in a structure.

Therefore, it is not practical to run something such as a micromechanics simulation during the evaluation of each candidate. However, advancements made in machine learning in the last decade creates the opportunity to embed surrogates of these multiscale material models within vehicle-level optimization while using significantly less computational resources.

Machine learning has been successfully applied within each of those two domains; the work outlined in this proposal would be the first use of machine learning in a commercial software to link these two domains. Machine learning would be used to develop surrogates of the HyperX analysis and optimization, with composite lamina properties as inputs to the models.

This would enable rapid design exploration and optimization with tailored material systems by providing accurate component performance and vehicle/system masses for each material candidate considered. Proposal Number: A1.

03-1010 Subtopic Title: Propulsion Efficiency - Propulsion Materials and Structures Proposal Title: Digital Twin and Thread Ecosystem for Automated ICME and Modeling Workflow Optimization Firm: Materials Data Management, Inc. Address: 3202 N. Meridian Street, Indianapolis, IN, 46208-4646 E-mail: TSearles@mdmi. com Address: 3202 N.

Meridian Street, Indianapolis, IN, 46208-4646 Phone: 317-708-4969 Business Official E-mail: PSearles@mdmi. com Address: 3202 N.

Meridian Street, Indianapolis, IN, 46208-4646 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 5 Technical Abstract (Limit 2000 characters): MDMi Modeling Hub (MMH) aims to integrate modeling, testing, design, and manufacturing data into a digital ecosystem, accelerating the transition from ideation to implementation.

By leveraging a robust and automated data management strategy, MMH will advance ICME and Digital Twin concepts, enabling experimental and virtual data to seamlessly drive model optimization and accuracy. In industries where production costs are high and performance is critical, benefits of modeling can be seen over the entire product lifecycle, reducing development costs and time-to-market.

The value of modeling is irrefutable and capable of broad organizational impact, yet challenges in standardizing usage and understanding limitations have hindered effective implementation and widespread adoption. Further, in the absence of data management, the full potential of modeling is never realized.

Some large organizations have developed tools to meet limited, highly specialized needs, the complex and resource-intensive nature of modeling creates a high barrier of entry that deters many organizations. There is a gap in commercial software that can simplify and automate multistep modeling and data storage processes. MMH has been designed to fill this gap.

In Phase 1, a prototype software framework will demonstrate a scalable, interoperable, and traceable modeling solution that allows the creation of simplified and standardized workflows that integrate diverse user-developed models (ranging from physics to ML-based models, supporting numerical, text, and traceability data).

MMH’s cloud-compatible approach will offer a holistic solution that can be configured to accelerate innovation throughout an organization. MMH forwards NASA goals of improving accessibility of data and analysis tools to drive collaboration to advance modeling. MMH will directly augment research within NASA’s Materials and Structures Division and significantly further NASA’s 2040 Vision.

Proposal Number: A1. 03-1012 Subtopic Title: Propulsion Efficiency - Propulsion Materials and Structures Proposal Title: Flexible CMC Structures for Propulsion Efficiency Firm: Physical Sciences Inc. Address: 20 New England Business Center, Andover, MA, 01810-1077 E-mail: rguarriello@psicorp. com Address: 20 New England Business Center, Andover, MA, 01810-1077 E-mail: marinelli@psicorp.

com Address: 20 New England Business Center, Andover, MA, 01810-1077 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 5 Technical Abstract (Limit 2000 characters): Physical Sciences Inc (PSI) will fabricate high temperature spring preloaders for turbomachinery seals from our flexible Carbon fiber-reinforced Silicon Carbide (C/SiC) Ceramic Matrix Composite (CMC) system.

The team will fabricate springs of different lengths, thicknesses, and stiffnesses with an accordion fold geometry and variable lengths. PSI will evaluate the springs’ mechanical performance at both ambient and elevated temperatures to model their mechanical response based on the different fabrication variables to meet NASA’s performance requirements for spring preloaders in turbomachinery sealing systems.

Seals have historically been a major area of concern with propulsion systems, both turbines and hypersonics, to prevent leaks and uncontrolled changes in pressure of the flight system. Existing sealing systems for these applications have an upper use temperature of ~2000 °F. Combustors can reach temperatures upwards of 3000 °F in J-class turbine engines, well beyond the upper use temperature of metallic alloys.

The High Mach Gas Turbine (HMGT) and Turbine Based Combined Cycle (TBCC) propulsion systems, currently being explored by NASA and AFRL for use in DARPA’s NextRS systems, will also require innovative higher temperature materials systems than metallic alloys can provide to reach the desired speeds. PSI’s flexible C/SiC CMCs are the most flexible CMCs available with active bend radii as small as 3. 5†and tailorable stiffness.

The flexible CMCs can be fabricated in complex geometries with bend radii as small as 1/16†for complex structures such as accordion fold spring preloaders. PSI’s Flexible CMC material has resilience in extended bend fatigue testing to a 3. 5†radius in ambient environments for thousands of cycles.

There is no measurable loss in the flexure of the material after the initial few cycles. PSI’s flexible CMCs have been tested under continuous actuation in highly aggressive oxidating environments at temperatures up to 5000 °F Proposal Number: A1.

03-1013 Subtopic Title: Propulsion Efficiency - Propulsion Materials and Structures Proposal Title: Novel Environmental Barrier Coatings for Ceramic Matrix Composites in Aero Engines Firm: Solution Spray Technologies LLC Address: 104 Timber Drive, Storrs, CT, 06268-1227 E-mail: ejordan@solutionspray. com Address: 104 Timber Drive, Storrs, CT, 06268-1227 Name: Balakrishnan Nair E-mail: bnair@solutionspray.

com Address: 104 Timber Drive, Storrs, CT, 06268-1227 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): NASA has a significant interest in technologies that can increase the fuel efficiency and power density of gas turbines in aero engines, which dominates purchase decisions. The path for efficiency improvement is through increasing the turbine inlet temperature.

Increased use of ceramic matrix composites (CMCs), specifically those based on silicon carbide (SiC), can increase inlet temperatures in excess of 2,700 F (1482 C) and reduce weight. However, SiC-based CMCs are susceptible to significant corrosion in water vapor present in combustion streams at such high temperatures.

Therefore, gas turbine components made of these materials require an environmental barrier coating (EBC) to protect them from water vapor. The current state-of-the art EBCs have an operating temperature limit of about 1300 C, above which they themselves experience significant corrosion in water vapor. They are also significantly corroded by calcium magnesium aluminosilicates (CMAS) resulting from dust and volcanic debris.

With NASA SBIR funding, a new EBC composition will be developed and demonstrated that is suitable for use at temperatures up to 1482oC. This composition will be selected from a new class of candidate EBC materials that have the potential for excellent matching of the thermal expansion coefficient to the SiC-based composites by altering the chemistry, resulting in improved durability.

We will down-select the best candidate from a few thermal expansion matched compositions from this materials family that has sufficient water vapor corrosion resistance and chemical stability against CMAS at 1482 C. A coating of the down-selected composition will be made through a novel plasma spray process.

The coating will then be tested in a highly realistic high velocity rig up to the target temperature of 1482 C, to demonstrate improved performance over state-of-the-art EBCs. This novel EBC technology is targeted at aero engines, as well as stationary gas turbines for utility-scale power. Proposal Number: A1.

03-1019 Subtopic Title: Propulsion Efficiency - Propulsion Materials and Structures Proposal Title: Multi-scale location-specific fatigue life prediction for additive propulsion components Small Business Concern Firm: QuesTek Innovations LLC Address: 1820 RIDGE AVE, EVANSTON, IL, 60201-3621 E-mail: pkotaru@questek. com Address: 1820 RIDGE AVE, EVANSTON, IL, 60201-3621 E-mail: pkotaru@questek.

com Address: 1820 RIDGE AVE, EVANSTON, IL, 60201-3621 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): To enable NASA’s technology roadmap for robust and efficient modeling and design of advanced propulsion system materials and structures, QuesTek (QT) will develop and demonstrate a multi-scale process-structure-property-performance modeling framework for aero propulsion component lifing.

QT will develop a state-of-the-art integrated computational materials engineering toolkit and implement it in the ICMD® software platform to enable NASA, the aerospace industry, and broader materials intensive industries to leverage accurate and predictive component scale lifing in an intuitive and collaborative cloud-based graphical user interface.

Additive manufacturing (AM) is key technology enabler for NASA to improve aero propulsion system efficiency, however, components in these systems are exposed to complex fatigue loading conditions, and paired with the inherent complexity of AM microstructures, durability is difficult to predict.

This lack of predictive power that currently exists for fatigue of AM aero propulsion components is a barrier to the broader adoption of the technology. QT will enable composition, process history, microstructure, and component geometry/loading conditions to be captured in a multi-scale PSPP framework to provide robust and efficient component lifing predictions. This will enable concurrent engineering of propulsion systems and alloys.

The framework will use CALPHAD based modeling to link composition and process history with microstructure evolution, physics-based mean field analytical modeling to link microstructure with tensile properties, crystal plasticity finite element method to link tensile properties and microstructure with fatigue properties, and Ansys’ nCode DesignLife, a component scale finite element method software to link fatigue properties with component scale lifing.

Machine learning will be used for reduced order surrogate modeling to enable uncertainty quantification and propagation through the model framework. Proposal Number: A1. 04-1038 Subtopic Title: Novel Aircraft Configurations for Electrified Aircraft Propulsion Proposal Title: UltraQuiet JetFoil-Enabled V/STOL Multi-Mission UAS Address: 109 Pointe Ldg, Crossville, Tennessee, 38555-2001 E-mail: mark@whisperaero.

com Address: 109 Pointe Ldg, Crossville, Tennessee, 38555-2001 E-mail: rebecca@whisperaero.

com Address: 109 Whisper Way, Crossville, TN, 38555-2201 Phone: 931-248-4008 Summary Details Estimated Technology Readiness Level(TRL Begin - TRL End): 3 - 4 Technical Abstract (Limit 2000 characters): Whisper Aero has developed unique Electric Ducted Fans that provide scale invariant thrust that has the same high efficiency and thrust to weight ratio characteristics at any size.

Because these propulsors are compact with low complexity they can be tightly integrated into emission-less electric aircraft concepts in compelling ways to achieve breakthrough performance, noise, and cost. A battery electric concept will be designed as a manned variant of a DoD hybrid electric cargo drone being developed by Whisper Aero as part of a recent STRATFI/OECIF award.

The proposed effort is a unique design effort with substantially different requirements to meet a General Aviation civil mission definition that can be in production by 2030. A unique characteristic of this design is the ability to perform eVTOL, eSTOL, and eCTOL missions at different gross weights with the same aircraft.

This enables a single aircraft product to have varying utility to trade off takeoff performance for added range or payload, depending on user needs. Leveraging the STRATFI drone learnings offers increased probability of achieving a certified aircraft by utilizing identical components arranged in a different configuration and with a different energy source (batteries instead of a hybrid turbogenerator).

Achieving dual use across aircraft product families has been a core goal of AFWERX as they’ve stimulated the eVTOL ecosystem. Commercialization success is further enhanced by leveraging the Phase II sub-scale test aircraft to align with delivery drone requirements to validate not only the concept feasibility and also yield an operational demonstrator that has additional product potential. Proposal Number: A1.

04-1045 Subtopic Title: Novel Aircraft Configurations for Electrified Aircraft Propulsion Proposal Title: Cost-Effective Electric Cargo Aircraft Firm: Wingborne Aeronautics Corporation Address: 865 Saint Charles Ave NE, Atlanta, GA, 30306-4128 Phone: 404-353-5601 Principal Investigator Name: Mark Kotwicz Herniczek E-mail: mark@wingborne-aero. com Address: 428 Burton Drive, Alpharetta, GA, 30009-2497 E-mail: brian@wingborne-aero.

com Address: 865 Saint Charles Ave NE, Atlanta, GA, 30306-4128 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): Regional air cargo operations are essential for logistics but face challenges due to high costs and low aircraft utilization.

Existing regional cargo aircraft, such as the Cessna 208 Caravan and Beechcraft 99, have high operating costs associated with fuel burn and maintenance of their aging airframes, yet cargo air carriers often rely on depreciated legacy aircraft because of the high acquisition costs of new aircraft. The proposed work focuses on the design of a novel, low-cost, autonomy-ready, electric aircraft optimized for regional air cargo operations.

Phase I will include market studies to define aircraft requirements, trade space exploration to evaluate conceptual designs and electric propulsion integration strategies, concepts of operations modeling, cost modeling, and exploration of certification pathways. The target market for the aircraft consists of regional cargo operators, feeder airlines, and government agencies needing affordable air logistics solutions.

The proposed work will accelerate the adoption of electrified autonomous cargo aircraft and increase the economic viability of the regional air cargo industry. Proposal Number: A1.

04-1052 Subtopic Title: Novel Aircraft Configurations for Electrified Aircraft Propulsion Proposal Title: The Annular-Wing VTOL Aircraft Address: 10 W HIGH ST, Watsonville, CA, 95076-3809 Address: 10 W High St, Watsonville, CA, 95076-3809 Address: 10 W High St, Watsonville, CA, 95076-3809 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): The Annular-Wing VTOL Aircraft introduces a redefinitive aerodynamic configuration built around a circular wing design that addresses critical limitations in existing electric vertical takeoff and landing (eVTOL) platforms.

Our innovation integrates a fixed-pitch coaxial lift system within an annular wing architecture, enabling 1,500 lb payload capacity—50% more than competing designs—while achieving exceptional energy efficiency of 2,800 J/lb-mile.

Key innovations include: (1) a propeller parking system that eliminates transition drag by aligning lift rotors with airflow during cruise; (2) below-fuselage propulsion that optimizes propwash utilization; (3) streamlined flight mode transitions without complex tilting mechanisms; and (4) hydrogen fuel cell integration capability for extended range operations.

Phase I funding will support high-fidelity CFD modeling, propeller parking mechanism development, control system refinement, and scaled prototype flight testing. Our 1-meter subscale prototype has already validated core aerodynamic principles through 50+ successful flight tests.

Primary markets include NASA applications (emergency response, scientific deployment), Advanced Air Mobility (4-6 passenger transport), medical evacuation, and defense/security operations. The unique combination of helicopter-class payload with fixed-wing efficiency positions this platform to capture significant market share within the projected $30. 8B eVTOL market by 2030.

Proposal Number: A1. 06-1009 Subtopic Title: Vertical Takeoff and Landing (VTOL) Vehicle Technologies - Vehicle Design Tool & Electric Powertrain Test Capability Proposal Title: Airfoil Data Analysis Software for Rotorcraft Design Address: 1600 Whipple Dr., Blacksburg, VA, 24060-2419 E-mail: pravetta@avec-engineering. com Address: 1600 Whipple Dr., Blacksburg, VA, 24060-2419 E-mail: cfrago@avec-engineering.

com Address: 1600 Whipple Dr., Blacksburg, VA, 24060-2419 # Summary Details Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): NASA is actively working on Vertical Takeoff and Landing (VTOL) Vehicle Technologies such as the Revolutionary Vertical Lift Technology (RVLT) project.

For the analysis/design of these types of vehicles, rotorcraft tools require aerodynamic properties of the rotor sections over -180 to +180 degrees of angle of attack and wide range of operating conditions covering all flight situations. This large amount of aerodynamic data is typically provided in the form of C81-formatted airfoil aerodynamic coefficient table files.

Thus, there is a need to generate these C81-formatted files using an automated computer tool. AVEC proposes the development of a software package for the generation of airfoil aerodynamic data using several analysis tools (XFOIL, OVERFLOW, MSES). In addition, the software will also include a database that allows the interactive visualization and manipulation of the data.

The software package will be run using a graphic user interface (GUI) with many capabilities to make the process fast, accurate and cost effective.

To this end, AVEC will leverage many tools developed over the last 20 years as part of many projects in aerodynamics and acoustics of propulsion systems, e.g. propellers, ducted fans, etc. In fact, using internal funds over the last ~3 years, AVEC has already started developing a GUI operated database for a large number of airfoil profiles and aerodynamic data.

Since the existing GUI already contains some of the features and capabilities requested in the solicitation, Phase I work can provide an efficient use of funds while also focusing specifically on addressing NASA’s requirements. Based on AVEC’s capabilities, experience, and existing tools, a beta version of the software package will be delivered at the end of Phase I. Proposal Number: A1.

06-1010 Subtopic Title: Vertical Takeoff and Landing (VTOL) Vehicle Technologies - Vehicle Design Tool & Electric Powertrain Test Capability Proposal Title: Hierarchical Flexible Toolset for Generating Airfoil Performance Tables for Aircraft Design Firm: Continuum Dynamics, Inc. Address: 34 Lexington Avenue, Ewing, NJ, 08618-2302 Phone: 609-538-0444 Principal Investigator E-mail: glen@continuum-dynamics.

com Address: 34 Lexington Avenue, Ewing, NJ, 08618-2302 E-mail: Melissa@continuum-dynamics.

com Address: 34 Lexington Ave, Ewing, NJ, 08618 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): Despite the capabilities and usability improvements of modern computational fluid dynamics software, rotary-wing aircraft design and analysis often uses lower fidelity methods that require pre-computed 2D airfoil data tables because these methods can provide adequate accuracy in a fraction of the setup and computation time.

The C81 data format has long been used by rotorcraft sizing, conceptual, and preliminary design tools to define airfoil lift, drag and moment as a function of angle of attack, Mach number, and Reynolds number.

Even though C81 tables have a long legacy of use, their generation, especially for new airfoil sections typical of modern Urban Air Mobility configurations, is far from routine given the need to cover 360o angle of attack over a range of Mach and Reynolds numbers – with manual tuning often used to fill-in missing data or remove questionable points.

The proposed effort by Continuum Dynamics, Inc., (CDI), seeks to build upon our decades of experience developing and using C81 tables for rotorcraft design and analysis to develop a software toolset tailored to automatically and robustly generating accurate and reliable C81 tables.

The toolset will feature a range of methods for automatically predicting single and multi-element airfoil section performance, and assembling the resulting C81 tables. In Phase I, a prototype tool with automatic grid generation, will be developed that launches, monitors, and post-processes airfoil performance predictions.

The tool will then assemble the desired C81 table from the database of predictions and experimental data, and provide uncertainty metrics to the user associated with the source of the data used. The tool will be built around CDI’s in-house 2D CFD solver that we use to generate 2D look-up tables, but within a framework flexible enough to support alternate CFD solvers.

Phase II will see software enhancement and generalization to support a variety of data and prediction generation sources. Duration: 6 Proposal Number: A1. 06-1011 Subtopic Title: Vertical Takeoff and Landing (VTOL) Vehicle Technologies - Vehicle Design Tool & Electric Powertrain Test Capability Proposal Title: PyFoil81: Rotorcraft Design Tool Airfoil Table Generator Firm: M4 Engineering, Inc. Address: 4020 Long Beach Bl.

, Long Beach, CA, 90807-2663 E-mail: tcuatt@m4-engineering. com Address: 4020 Long Beach Bl. , Long Beach, CA, 90807-2663 E-mail: twinter@m4-engineering.

com Address: 4020 Long Beach Blvd, Long Beach, CA, 90807-2683 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): The Revolutionary Vertical Lift Technology (RVLT) Program is exploring an open design space for novel VTOL aircraft configurations.

Highly efficient and lightweight electric motors paired with the increasing energy density of batteries are enabling new aircraft concepts such as Distributed Electric Propulsion and eVTOL, which exploit new technologies’ advantages to improve existing missions and enable whole new missions such as Urban Air Mobility.

Flight for eVTOLs creates new analytical challenges: rotors are designed with small chord and diameter as well as unconventional twist profiles, and with wider operational RPM and advance ratio ranges, can have larger regions of reversed flow.

To meet this departure from traditional rotor aerodynamics in context of the high impact of aeropropulsive efficiency on mission capability, M4 proposes a lightweight Python software, PyFoil81, capable of efficiently analyzing and tabulating airfoil data from a variety of flow regimes.

It will efficiently handle user inputs, airfoil rediscretization and modification, API to/from multiple aero solvers, and a data blending tool to create composite C81 airfoil data tables from various data sources. Proposal Number: A1.

06-1019 Subtopic Title: Vertical Takeoff and Landing (VTOL) Vehicle Technologies - Vehicle Design Tool & Electric Powertrain Test Capability Proposal Title: Automated Airfoil Table Generation for VTOL Aircraft Firm: Advanced Rotorcraft Technology Address: 46757 FREMONT BLVD, FREMONT, CA, 94538-6539 E-mail: chengjian. he@flightlab.

com Address: 46757 Fremont Blvd, Fremont, CA, 94538-6539 # Business Official Name: Douglas Carrig E-mail: doug. carrig@flightlab. com Address: 46757 FREMONT BLVD, FREMONT, CA, 94538-6539 Estimated Technology Readiness Level(TRL Begin - TRL End): 1 - 5 Technical Abstract (Limit 2000 characters): The design and development of VTOL air vehicles, especially AAM, is making rapid progress with numerous innovative configurations.

The industry is, however, facing serious challenges in achieving its goal toward affordable high performance/low noise VTOL that can be timely certified for operation. Design and analysis of modern VTOL has been a major hurdle due to extremely high computational demands. Comprehensive rotorcraft analysis tools are widely used for VTOL design and analysis.

To manage costs, comprehensive tools use C81 airfoil tables for quick turnaround. Hence, the ability to quickly and accurately generate C81 tables is vital. The proposed work aims at creating a high fidelity airfoil table generator to effectively support VTOL design.

The tool to be developed will be versatile in terms of supporting the unique requirements of VTOL design and analysis. The tool will also be streamlined, efficient, automated along with a friendly graphical user interface. Proposal Number: A1.

08-1014 Subtopic Title: Aeronautics Ground Test and Measurement Technologies: Diagnostic Systems for High-Speed Flows and Icing Proposal Title: A Long-wavelength IR Sensor for Water Drop Temperature Measurement Firm: Spectral Energies, LLC Address: 4065 Executive Dr, Beavercreek, OH, 45430-1062 Phone: 937-266-9570 Principal Investigator E-mail: naibo. jiang@spectralenergies.

com Address: 4065 Executive Dr, Beavercreek, OH, 45430-1062 E-mail: admin1@spectralenergies.

com Address: 4065 Executive Dr, Beavercreek, OH, 45430-1062 Estimated Technology Readiness Level(TRL Begin - TRL End): 3 - 4 Technical Abstract (Limit 2000 characters): This proposed research aims to develop an LWIR imaging sensor to enable real-time, in-situ measurements of temperatures and size distributions of airborne supercooled water droplets. The proposed sensor will use an LWIR camera for 2D imaging of the water droplets.

By calibrating temperature and intensity of small water drops in the icing tunnel, the water droplets will be imaged to obtain size distribution information. The temperature of the water droplets will be determined based on the LWIR emission intensity. Phase I will focus on the design, fabrication, and demonstration of the sensor system in a research icing tunnel.

Phase II will involve the application and testing of the sensor system in NASA’s icing wind tunnel. Proposal Number: A1. 09-1008 Subtopic Title: Zero-Emissions Technologies for Aircraft Proposal Title: HYDRATE: A Zero-Emission Direct Drive Parallel Hybrid Turbofan for Personal Jets Small Business Concern Address: 11 Hidden Brick Road, Hopkinton, MA, 01748-2663 E-mail: ian@maglevaero.

com Address: 11 Hidden Brick Road, Hopkinton, Massachusetts, 01748-2663 E-mail: josh@maglevaero. com Address: 12 Channel St, Boston, MA, 02210-2323 Estimated Technology Readiness Level(TRL Begin - TRL End): 2 - 3 Technical Abstract (Limit 2000 characters): HYDRATE represents a transformative leap in zero-emission aviation propulsion, integrating a hydrogen-burning regenerative turbine with MagLev Aero’s proprietary maglev rim drive.

This parallel hybrid system optimizes fuel efficiency, reducing cruise fuel consumption by over 20%, while increasing bypass ratios and thermal efficiency—key limitations in current small turbofans. Unlike traditional hybridization efforts focused on large commercial aircraft with marginal efficiency gains, HYDRATE targets the underserved Very Light Jet (VLJ) market, where existing propulsion remains outdated.

By leveraging magnetic gearing, tip-driven assistance, and regenerative energy use, the system achieves superior throttle response, reduced complexity, and increased operational flexibility. Quantitatively, the design enables optimized thrust distribution throughout flight, compensating for altitude variations and improving safety.

The approach offers a scalable pathway toward zero-emission propulsion with near-term applications in personal jets and potential expansion into larger commercial aviation through NASA’s HyTEC initiative, setting a new standard for sustainable, high-performance flight. Duration: 6 Proposal Number: A1.

11-1010 Subtopic Title: Health Management and Sensing Technologies for Sustainable Aviation Vehicles Proposal Title: Sustainable Aviation Prognostics and Predictive Health Integrated Reliability Engine Firm: Cybernet Systems Corporation Address: 3741 Plaza Drive , Ann Arbor, MI, 48108-1655 E-mail: proposals@cybernet. com Address: 3741 Plaza Drive , Ann Arbor, MI, 48108-1655 E-mail: proposals@cybernet.

com Address: 3741 Plaza Drive , Ann Arbor, MI, 48108-1655 Estimated Technology Readiness Level(TRL Begin - TRL End): 3 - 6 Technical Abstract (Limit 2000 characters): As NASA pursues net-zero aviation emissions by 2050, new hybrid-electric, all-electric, and hydrogen aircraft present unique health management challenges. These novel propulsion systems require innovative approaches to detect anomalies in complex integrated architectures.

Cybernet proposes SAPPHIRE (Sustainable Aviation Prognostics and Predictive Health Integrated Reliability Engine) to address these needs. SAPPHIRE provides health management specifically for sustainable aviation