Effects of wing warp on the lift, drag, and static longitudinal stability characteristics of an aircraft configuration having an arrow wing of aspect ratio 1.86 at Mach numbers from 1.1 to 1.7 Page: 2 of 28
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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
EFFECTS OF WING WARP ON TEE LIFT, DRAjG, AND STATIC
LONGITUDINAL STABILITY CHARACTERISTICS OF AN
AIRCRAFT CONFIGURATION HAVING AN ARROW
WING OF ASPECT RATIO 1.86 AT MACK
NUMBERS FROM 1.1 TO 1.7
By Warren Gillespie, Jr.
The results of a free-flight investigation to determine the effect
of wing warp on the lift, drag, and static longitudinal stability charac-
teristics of a low-drag aircraft configuration employing an arrow wing of
aspect ratio 1.86 are presented. The mean surface shape of the warped
wing was derived from a lifting surface theory for a design lift coeffi-
cient of 0.2 at a Mach number of 1.57. Data from a similar plane-wing
model provided a basis for comparison. Lift, drag, and pitching-moment
coefficients were obtained at Mach numbers from 1.1 to 1.7, and at
Reynolds numbers from 5 x 10 to 11 x 10 per foot of length.
Wing warp reduced the axial-force and total drag coefficients above
a lift coefficient of 0.2. The maximum lift-drag ratios of the warped-
wing model were 10 to 4 percent higher than those of the plane-wing model.
However the maximum ratios of lift coefficient raised to the one-half
power divided by the corresponding drag coefficient were 8 to 9 percent
lower for the warped-wing model.
Two methods of wing design appear capable of improving the perform-
ance of supersonic aircraft. Results obtained to date by the method of
wing warp (refs. 1 to 6) indicate that this method is effective up to
low supersonic speeds and design lift coefficients less than 0.5. The
results obtained by the method of inboard chord extension refss. 7 to 10)
indicate that both range and maximum speed can be increased at the higher
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Gillespie, Warren, Jr. Effects of wing warp on the lift, drag, and static longitudinal stability characteristics of an aircraft configuration having an arrow wing of aspect ratio 1.86 at Mach numbers from 1.1 to 1.7, report, August 30, 1957; (digital.library.unt.edu/ark:/67531/metadc63619/m1/2/: accessed February 15, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.