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Flow-Field Measurement of a Hybrid Wing Body Model with Blown FlapsIn this paper we describe flow-field measurements obtained in the wake of a full-span Hybrid Wing Body model with internally blown flaps. The test was performed at the NASA Langley 14 x 22 Foot Subsonic Tunnel at low speeds. Off-body measurements were obtained with a 7-hole probe rake survey system. Three model configurations were investigated. At 0deg angle of attack the surveys were completed with 0deg and 60deg flap deflections. At 10deg angle of attack the wake surveys were completed with a slat and a 60deg flap deflection. The 7-hole probe results further quantified two known swirling regions (downstream of the outboard flap edge and the inboard/outboard flap juncture) for the 60deg flap cases with blowing. Flow-field results and the general trends are very similar for the two blowing cases at nozzle pressure ratios of 1.37 and 1.56. High downwash velocities correlated with the enhanced lift for the 60deg flap cases with blowing. Jet-induced effects are the largest at the most inboard station for all (three) velocity components due in part to the larger inboard slot height. The experimental data are being used to improve computational tools for high-lift wings with integrated powered-lift technologies.
Document ID
20080034481
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Lin, John C. (NASA Langley Research Center Hampton, VA, United States)
Jones, Gregory S. (NASA Langley Research Center Hampton, VA, United States)
Allan, Brian G. (NASA Langley Research Center Hampton, VA, United States)
Westra, Bryan W. (Northrop Grumman Corp. El Segundo, CA, United States)
Collins, Scott W. (Northrop Grumman Corp. El Segundo, CA, United States)
Zeune, Cal H. (Air Force Research Lab. Wright-Patterson AFB, OH, United States)
Date Acquired
August 24, 2013
Publication Date
August 18, 2008
Subject Category
Aerodynamics
Meeting Information
Meeting: 26th AIAA Applied Aerodynamics Conference
Location: Honolulu, HI
Country: United States
Start Date: August 18, 2008
End Date: August 21, 2008
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 561581.02.08.07.20.02
Distribution Limits
Public
Copyright
Public Use Permitted.

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