Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail Page: 2 of 27
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TECH LIBRARY KAFB, NM
NACA RM A9Flk SHIP""II
NATIONAL ADVISORY CCIMfTTEE FOR AERONAUTICS
AERODYNAMIC STUDY OF A WING-FUSELAGE COMBINATION EMPLOYING A WING
SWEPT BACK 63o.- AERODYNAMIC CHARACTERISTICS IN SIDESLIP OF A
LARGE-SCALE MODEL HAVING A 630 SWEPT-BACK VERTICAL TAIL
By Gerald M. McCormack
An investigation has been conducted to determine the effects of a
vertical tail having the leading edge swept back 630 on the aerodynamic
characteristics of a wing-fuselage combination employing a wing with the
leading edge swept back 630. The aerodynamic characteristics in side-
slip with and without the vertical tail are presented. Included also are
the rudder effectiveness and the rudder hinge-moment characteristics.
At angles of attack from 00 to 120, the effectiveness of the verti-
cal tail was maintained to an angle of sideslip of 250 (the highest
tested). At an angle of attack of 210, however, effectiveness was main-
tained only to an angle of sideslip of about 7o; beyond 7 the directional
stability was irregular.
The rudder was effective throughout the range of angles of attack
and of angles of sideslip tested. At an angle of attack of 21, however,
at angles of sideslip greater than about 90, rudder effectiveness was
considerably less than at the lower angles.
The experimental characteristics are compared with characteristics
computed theoretically in order to provide a basis for estimating the
effects of geometric changes of the vertical tail.
A possible aircraft configuration suitable for flight at Mach numbers
up to about 1.5 is undergoing study in the research facilities of the Ames
Aeronautical Laboratory to provide information relative to its aerodynamic
behavior over a range of Reynolds numbers and Mach numbers. The configu-
ration is based on the principles outlined in reference 1 which indicate
that aircraft employing highly swept slender wings should be capable of
relatively efficient flight (L~D/ 10) at moderate supersonic speeds. The
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McCormack, Gerald M. Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail, report, October 7, 1949; (digital.library.unt.edu/ark:/67531/metadc58396/m1/2/: accessed January 18, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.