Static 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.
Hybrid Wing Body Model Identification Using Forced-Oscillation Water Tunnel Data
2014
13 pages
Report
No indication
English
Aircraft , Test Facilities & Equipment , Body-wing configurations , Aircraft models , Scale models , Angle of attack , Pitching moments , Forced vibration , Water tunnel tests , Subsonic wind tunnels , Wind tunnel tests , Unsteady aerodynamics , Dynamic tests , Static tests , Harmonic analysis , Mathematical models , Performance prediction , Flow visualization
Hybrid Wing Body Model Identification Using Forced-Oscillation Water Tunnel Data (AIAA 2014-2197)
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