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Hybrid Wing Body Model Identification Using Forced-Oscillation Water Tunnel DataStatic and dynamic testing of the NASA 0.7 percent scale Hybrid Wing Body (HWB) configuration was conducted in the Rolling Hills Research Corporation water tunnel to investigate aerodynamic behavior over a large range of angle-of-attack and to develop models that can predict aircraft response in nonlinear unsteady flight regimes. This paper reports primarily on the longitudinal axis results. Flow visualization tests were also performed. These tests provide additional static data and new dynamic data that complement tests conducted at NASA Langley 14- by 22-Foot Subsonic Tunnel. HWB was developed to support the NASA Environmentally Responsible Aviation Project goals of lower noise, emissions, and fuel burn. This study also supports the NASA Aviation Safety Program efforts to model and control advanced transport configurations in loss-of-control conditions.
Document ID
20150000559
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Murphy, Patrick C.
(NASA Langley Research Center Hampton, VA, United States)
Vicroy, Dan D.
(NASA Langley Research Center Hampton, VA, United States)
Kramer, Brian
(Rolling Hills Research Corp. El Segundo, CA, United States)
Kerho, Michael
(Rolling Hills Research Corp. El Segundo, CA, United States)
Date Acquired
January 16, 2015
Publication Date
June 16, 2014
Subject Category
Aircraft Design, Testing And Performance
Aircraft Stability And Control
Report/Patent Number
NF1676L-17791
Meeting Information
Meeting: AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014)
Location: Atlanta, GA
Country: United States
Start Date: June 16, 2014
End Date: June 20, 2014
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 284848.02.05.07.01
Distribution Limits
Public
Copyright
Public Use Permitted.
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