Blown airfoil CFD. This task will perform computational fluidic dynamic (CFD) analysis on a blown wing configuration to determine aero-propulsive performance. Distributed electric propulsion (DEP)…

This federal contract award, with a ceiling value of $47,832.75, was issued by the National Aeronautics and Space Administration (NASA) Langley Research Center to the National Institute of Aerospace Associates (NIA), a non-profit research institute, to perform computational fluid dynamics (CFD) analysis on a "blown wing" aircraft configuration with distributed electric propulsion (DEP). The goal is to evaluate the aero-propulsive performance characteristics of this DEP wing design, which aims to achieve very high lift at low speeds while also maintaining high cruise efficiency and excellent control across the flight envelope. This task extends previous analysis on a related geometry, with modifications to the propulsor locations, wing slot configurations, and other parameters. NIA has subcontracted a portion of this work to Coflow Jet, LLC, a small disadvantaged business, to assist with the CFD modeling and simulations. This contract does not have a set-aside designation and is structured as a cost-plus-fixed-fee delivery order under a larger, open-ended contract vehicle. The research supports NASA's ongoing efforts to advance electric and hybrid-electric propulsion technologies for future aircraft.

Blown airfoil CFD. This task will perform computational fluidic dynamic (CFD) analysis on a blown wing configuration to determine aero-propulsive performance. Distributed electric propulsion (DEP) enables a high degree of coupling between the aerodynamics and propulsion characteristics of aircraft wing systems. Tight coupling of these two disciplines offer opportunities to improve the performance and achieve capabilities that can t be achieved with isolated wing and propulsion solutions. Higher-order analysis using CFD tools is required to capture these highly coupled effects with analysis tools that have been calibrated to validation datasets from prior aero-propulsive wind tunnel tests. Analysis of specific DEP wing systems is desired to improve the state of the art to achieve very high lift at low speeds, at even static conditions while entraining flow to maximize the wing lifting characteristics. At the same time high cruise efficiency is desired, along with excellent control characteristics throughout the flight envelope. This research will investigate specific DEP configuration to better understand the aero-propulsive characteristics. Existing analysis was performed on a geometry. This current statement of work extends previous work with modifications to the locations and shape of the propulsors, slot locations, and wing.