Collection of zero-lift drag data on bodies of revolution from free-flight investigations Page: 2 of 374
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2 NACA TN 4201
they represented. In view of the large amount of data available and of
the comparative obscurity of a large part of it, it was felt that a
collection of such data presented in a standard form would be of aid to
the aircraft and missile designers.
It is hoped that this collection will be useful in several ways.
The large number of shapes presented herein may allow the designer to
estimate easily the drag of a desired shape by a simple comparison.
Supplementary data and theoretical estimates have been provided to
facilitate the determination of the body pressure drags from the measured
total drags. Summary plots and discussions have been included to provide
the user with a unified and broad picture of the effects of body geometry
on zero lift drag.
d maximum diameter
Z/d fineness ratio
r/R ratio of body radius at any station to maximum body radius
x/1 ratio of distance measured from apex of nose to total body
Sb/A ratio of body wetted area to body frontal area (actual values
calculated from expression C 42/d 1 r Rd which is
Cf 00 R Z
correct relationship between friction coefficient Cf based
on wetted area and friction drag coefficient CDf based on
body frontal area)
Sf/A ratio of fin wetted area to body frontal area
Ab/A ratio of body base area to body frontal area
Ob body slope at x/I = 1 (slope is always negative but is
expressed as positive)
R Reynolds number based on body length, pU
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Stoney, William E., Jr. Collection of zero-lift drag data on bodies of revolution from free-flight investigations, report, September 3, 1957; (https://digital.library.unt.edu/ark:/67531/metadc56974/m1/2/: accessed April 20, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.