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Experimental study of the interaction between the wing of a subsonic aircraft and a nacelle of a high by-pass ratio engineThe oncoming of a new generation of subsonic transport aircraft (with supercritical wing and high by-pass ratio turbofans) led to an experimental study of wing nacelle jet pylon interference in transonic flow. To this end, a test set-up was developed at the ONERA S3Ch wind tunnel. The nacelle models represent a turbofan by means of two compressed air jets. The scale is 1/18.5. The nacelles are fixed on a thrust balance measuring afterbody thrust and discharge coefficients. The wing is located between the sidewalls of the test section. Pressures are measured through 456 holes located on 8 airfoils. Drag coefficient of the wing is obtained by wake survey. The following parameters can vary (1) wing/nacelle position; (2) upstream Mach number (from 0.3 to 0.8); (3) jet pressure ratio; (4) with/without pylon and (5) type of nacelle. Wing nacelle interference can be studied by means of total thrust drag analysis as a functon of the various parameters. The test set-up is described and examples of results are presented.
Document ID
19810018505
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Levart, P. (NASA Headquarters Washington, DC United States)
Date Acquired
September 4, 2013
Publication Date
July 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-76606
Accession Number
81N27043
Funding Number(s)
CONTRACT_GRANT: NASW-3198
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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