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The effects of configuration changes on the aerodynamic characteristics of a full-scale mockup of a light twin engine airplaneWind tunnel tests of a full-scale model of a light twin engine aircraft were conducted. The angle of attack was varied from minus 4 degrees to plus 20 degrees. The sideslip range was plus or minus 8 degrees. Thrust coefficients were 0, 0.20, and 0.44. Tests were made with various nacelle configurations, modes of propeller rotation, orientation of the thrust axis, and airfoil section at Reynolds numbers of 2.96 times one million amd 2.05 times one million.
Document ID
19730007285
Document Type
Other - NASA Technical Note (TN)
Authors
Fink, M. P. (NASA Langley Research Center Hampton, VA, United States)
Shivers, J. P. (NASA Langley Research Center Hampton, VA, United States)
Greer, H. D. (NASA Langley Research Center Hampton, VA, United States)
Megrail, J. L. (Army Air Mobility Res. and Develop. Lab. Fort Eustis, Va., United States)
Date Acquired
September 2, 2013
Publication Date
September 1, 1972
Subject Category
Aircraft
Report/Patent Number
NASA-TN-D-6896
L-8375
Accession Number
73N16012
Funding Number(s)
PROJECT: RTOP 760-60-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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