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Turbine Powered Simulator Calibration and Testing for Hybrid Wing Body Powered Airframe IntegrationPropulsion airframe integration testing on a 5.75% scale hybrid wing body model us- ing turbine powered simulators was completed at the National Full-Scale Aerodynamics Complex 40- by 80-foot test section. Four rear control surface con gurations including a no control surface de ection con guration were tested with the turbine powered simulator units to investigate how the jet exhaust in uenced the control surface performance as re- lated to the resultant forces and moments on the model. Compared to ow-through nacelle testing on the same hybrid wing body model, the control surface e ectiveness was found to increase with the turbine powered simulator units operating. This was true for pitching moment, lift, and drag although pitching moment was the parameter of greatest interest for this project. With the turbine powered simulator units operating, the model pitching moment was seen to increase when compared to the ow-through nacelle con guration indicating that the center elevon and vertical tail control authority increased with the jet exhaust from the turbine powered simulator units.
Document ID
20160007820
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Shea, Patrick R. (NASA Langley Research Center Hampton, VA, United States)
Flamm, Jeffrey D. (NASA Langley Research Center Hampton, VA, United States)
Long, Kurtis R. (NASA Ames Research Center Moffett Field, CA, United States)
James, Kevin D. (NASA Ames Research Center Moffett Field, CA, United States)
Tompkins, Daniel M. (Boeing Aerospace Co. Huntington Beach, CA, United States)
Beyar, Michael D. (Boeing Aerospace Co. Huntington Beach, CA, United States)
Date Acquired
June 22, 2016
Publication Date
January 4, 2016
Subject Category
Aerodynamics
Aircraft Design, Testing And Performance
Report/Patent Number
NF1676L-23158
Meeting Information
Meeting: AIAA SciTech 2016
Location: San Diego, CA
Country: United States
Start Date: January 4, 2016
End Date: January 8, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 338881.02.27.07.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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