Summary of Data Relating to the Effects of Wing Machine-Gun and Cannon Installations on the Aerodynamic Characteristics of Airplanes Page: 4 of 70
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V1The data presented herein were obtained from two-
dimensional wind-tunnel tests of rectangular wins,
three-dimensional wind-tunnel tests of scale models,
and full-scale wind-tunnel and flight tests of airplanes.
For the two-dimensional tests, the drag was determined
by the wake-survey method and lift was determined bysection lift coefficient
section profile-drag coefficient
incremental wing-gun drag coefficient based on
local wing chord squared
S(OCnodel + guns CDmodel
number of gums
local wing.chord at center of gun installation
wing area
maximum win: thickness
height of :in-rorit cfningl
extenalon of gun or cancn LLhead of wing
gun-port inlet area
exSt area of gun duct
increment (+) or decrement (-) in maximum
lift coefficisnt
Re vnolds number
angular deflection of flap
free-stileam velocity
gun-port inlet velocity
TESTS
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Quinn, John H., Jr. Summary of Data Relating to the Effects of Wing Machine-Gun and Cannon Installations on the Aerodynamic Characteristics of Airplanes, report, January 1945; (https://digital.library.unt.edu/ark:/67531/metadc62430/m1/4/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.