As part of a collaborative effort between Boeing and NASA on the development of the Hybrid Wing Body (also known as Blended Wing Body) configuration, one of the key areas identified for detailed study was the propulsion airframe integration with the goal to demonstrate engine operability at low speed design and off-design conditions up to a Technical Readiness Level (TRL) 4. To facilitate these technology demonstrations, Boeing and NASA agreed to design, build, and test Boeing's Preferred System Concept (PSC) Blended Wing Body aircraft A low speed wind tunnel model was designed and fabricated and a test program was developed in order to investigate three key objectives. The first was the development of the leading edge high lift system to increase the maximum coefficient of lift (CLmax). The second was characterization and mitigation of adverse propulsion/airframe integration induced inlet flow distortion. The third was characterization of power-on effects to increase pitching moment to enable take off rotation. The low speed wind tunnel test program extended from July 2014 through August 2015.
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