EFFECTS of AFT-FUSELAGE-MOUNTED NACELLES on the SUBSONIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS of a TWIN-Turbojeqt AIRPLANE by Lawrence E
https://ntrs.nasa.gov/search.jsp?R=19670003847 2020-03-24T02:31:03+00:00Z EFFECTS OF AFT-FUSELAGE-MOUNTED NACELLES ON THE SUBSONIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A TWIN-TURBOJEqT AIRPLANE by Lawrence E. Putndm and Charles D. Trescot, Jr. .., , .. : ., '. ,.p, .*/-- Langley Reseurch Center ,,. ,>id. c rd .,,.& t.d\ , ';:. ,;c;C'>3 Langley Station, Hampton, Vu. ,z,, . ., .bz$$Y' ,.\. ~jq v;y I, ,,;- -.;;.;r .8';:"''/ (t ;;.; ~~ ..',-'.....-.,7 il . si h '/ .I. ;I i <, :,, ,:>- - .. *.-a__ NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. DECEMBER 1966 ) I [ TECH LIBRARY KAFB, NM NASA TN D-3781 EFFECTS OF AFT-FUSELAGE-MOUNTED NACELLES ON THE SUBSONIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A TWIN - TURBOJE T AIRPLANE By Lawrence E. Putnam and Charles D. Trescot, Jr. Langley Research Center Langley Station, Hampton, Va. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and Technical Information Springfield, Virginia 22151 - Price $2.50 EFFECTS OF AFT-FUSELAGE-MOUNTED NACELLES ON THE SUBSONIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A TWIN-TURBOJET AIRPLANE By Lawrence E. Putnam and Charles D. Trescot, Jr. Langley Research Center SUMMARY An investigation has been made in the Langley 26-inch transonic blowdown tunnel to determine the effects of aft-fuselage-mounted nacelles on the aerodynamic characteristics of a twin-turbojet airplane. The tests were made over a Mach number range from 0.63 to 0.82, at Reynolds numbers (based on wing mean aerodynamic chord) from 2.79 X 106 to 3.94 X lo6, and at angles of attack from -2' to 6O. The investigation was undertaken pri- marily to determine the effects of nacelle incidence, nacelle longitudinal location, nacelle cant angle, and modifications to the local area distribution on the lift, drag, and pitching- moment characteristics of the airplane configuration.
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