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Analysis of Mach number 0.8 turboprop slipstream wing/nacelle interactionsData from wind tunnel tests of a powered propeller and nacelle mounted on a supercritical wing are analyzed. Installation of the nacelle significantly affected the wing flow and the flow on the upper surface of the wing is separated near the leading edge under powered conditions. Comparisons of various theories with the data indicated that the Neumann surface panel solution and the Jameson transonic solution gave results adequate for design purposes. A modified wing design was developed (Mod 3) which reduces the wing upper surface pressure coefficients and section lift coefficients at powered conditions to levels below those of the original wing without nacelle or power. A contoured over the wing nacelle that can be installed on the original wing without any appreciable interference to the wing upper surface pressure is described.
Document ID
19810021547
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Welge, H. R. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Neuhart, D. H. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Dahlin, J. A. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Date Acquired
September 4, 2013
Publication Date
August 6, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-166214
ACEE-25-FR-1564
Accession Number
81N30085
Funding Number(s)
CONTRACT_GRANT: NAS2-10881
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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