Integrated High Lift Propulsor

Wayfarer Aircraft and Embry-Riddle Aeronautical University propose to use a 35% scale aircraft to gather aerodynamic flight test data fora novel type of distributed electric propulsion called the Integrated High Lift Propulsor (IHLP). The IHLP substantially increases cruise efficiency and reduces the thrust and power required for lift augmentation via blowing. As a fundamental aerodynamic device, the IHLP is applicable to many aircraft types, sizes, and missions, including uncrewed and piloted Advanced Air Mobility, public safety, and military applications. The overall program will characterize the aerodynamic performance of the IHLP with variation of key parametersusing a flexible design that enablesrapid between-flight configuration changes. Automated control effector inputs for system identification and a research quality instrumentation system will be used to characterizeaero-propulsive interaction. The incremental effects of the modification will be demonstrated by collecting both 35% scale and full-scale baseline flight test data, using Embry-Riddlesexisting instrumented research aircraft. The flight test program will cleartechnical risk and validate key technical objectives to proceed to full-scale flight test andcommercial adoption. The research program will also advance flight test techniques for aircraft with strong aero-propulsive coupling and provide high-quality experimentaldata. This data, combined with Wayfarers CFD and wind tunnel data,will validate and improve design and analysis tools used by NASA and industry. This Phase IIprojectwill leverage Wayfarers CFD and wind-tunnel based IHLP research combined with Embry-Riddles extensive hybrid/electric flight research experience and capability to gather high quality, full scale representative experimental datawith broad industry relevance. The Integrated High Lift Propulsor (IHLP) is a cruise-efficient form of Distributed Electric Propulsion with substantial aircraft benefits compared to current alternatives:   25% or more reduction in thrust and power for a given level of lift augmentation 35% or more mission energy savings for equal payload and range due to the cruise efficient design 50% reduction in electric motor weight, by reducing total motor torque   As a fundamental aerodynamic device, the IHLP is applicable to a wide variety of advanced hybrid / electric aircraft, including both new clean sheet designs and modifications or derivatives of existing aircraft.   The Integrated High Lift Propulsor will be broadly beneficial to the burgeoning Advanced Air Mobility market by offering significantly improved performance and efficiency combined with reduced emissions for a wide variety of aircraft. The Phase II project objects are to Modify a 35% scale research aircraft to gather full-scale representative flight research data  Characterize key IHLP performance data, validate key commercial metrics, and retire technical risk  Compare flight research data to Phase I aerodynamic predictions, company CFD, and wind tunnel data to validate and inform predictive tools and methods   Deliverables to NASA include: Design and descriptive details of the aircraft modifications to enable IHLP flight research objectives Comparison of baseline experimental aerodynamic data at full- and 35% scale Experimental aerodynamic data of the IHLP modified aircraft with extrapolation to full scale Comparison of experimental aerodynamic data of the IHLP modified research aircraft to predictions including Phase I data, company CFD, and wind tunnel data from related research. As-flown test plans including test matrix and test procedures

The proposed research 1) supports the objectives of the NASA ARMD Strategic Implementation Plan for ultra efficient subsonic aircraft in addition to supporting safe, quiet and affordable Advanced Air Mobility (AAM) vehicles, 2) advances technology to increase aircraft efficiency and reduce GHG (NASA Climate Action Plan Priority 5), and 3) supplies research quality validation data for the Transformational Tools and Technologies Project (TTT) The IHLP substantially increases cruise efficiency while reducing the thrust and power required for Distributed Electric Propulsion, resulting in higher performance, more efficient and more economical aircraft in defense, public safety roles such as disaster response and air ambulance, and many civil markets including super STOL, thin-haul, regional mobility, and short haul cargo.

This is early/mid-stage (TRL 5) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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