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
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
I&APaa L iusaAss&a 's.As &, ni.g
NACA RM L7Gl2 014478 4
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
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
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 July 15, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.