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Experiment Design for Complex VTOL Aircraft with Distributed Propulsion and Tilt WingSelected experimental results from a wind tunnel study of a subscale VTOL concept with distributed propulsion and tilt lifting surfaces are presented. The vehicle complexity and automated test facility were ideal for use with a randomized designed experiment. Design of Experiments and Response Surface Methods were invoked to produce run efficient, statistically rigorous regression models with minimized prediction error. Static tests were conducted at the NASA Langley 12-Foot Low-Speed Tunnel to model all six aerodynamic coefficients over a large flight envelope. This work supports investigations at NASA Langley in developing advanced configurations, simulations, and advanced control systems.
Document ID
20150006024
Document Type
Conference Paper
Authors
Murphy, Patrick C. (NASA Langley Research Center Hampton, VA, United States)
Landman, Drew (Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
April 21, 2015
Publication Date
January 5, 2015
Subject Category
Aerodynamics
Report/Patent Number
NF1676L-18953
Meeting Information
AIAA SciTech 2015 Meeting(Kissimmee, FL)
Funding Number(s)
WBS: WBS 794072.02.07.06.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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