Supplementary Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane in the Swept-Wing Configuration with Slats Extended Page: 3 of 17
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NACA RM SL51G19
moments of inertia about X, Y,
and Z body axes,
inertia yawing moment parameter
inertia rolling-moment parameter
inertia pitching-moment parameter
air density, slugs per cubic feet
relative density of airplane m
configuration but unsatisfactory for the swept-wing configuration.
Subsequent to completion of this investigation, information supplied by
the contractor indicated that the XF1OF-1 airplane was to be equipped
with full-span slats, and, inasmuch as analysis indicated a possible
favorable effect of slats for the XF10OF-1 design, supplementary model
tests were performed for the swept-wing version to evaluate their effect.
b wing span, feet
S wing area, square feet
c mean geometric chord, feet
x ratio-of distance of center of gravity rearward of leading
c edge of mean geometric chord to mean geometric chord
ratio of distance between center of gravity and fuselage
c reference line to mean geometric chord (positive when center
of gravity is below fuselage reference line)
m mass of airplane, slugs
IX, Iy, IZ
IX - Iy
IZ - I
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Berman, Theodore. Supplementary Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane in the Swept-Wing Configuration with Slats Extended, report, July 24, 1951; (digital.library.unt.edu/ark:/67531/metadc65355/m1/3/: accessed December 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.