Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds Page: 3 of 20
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2 ) NACA RM No. L6J16
In order to obtain information relative to the drag of wings
at supersonic speeds a series of tests are being conducted by the
Langley Pilotless Aircraft Research Division at Wallops Island, Va.,
of rocket-propelled bodies, carrying wings of various sweepback
angles A and aspect ratios A. Results are presented herein of
drag tests of rectangular and swept-back NACA 65-009 airfoils of
aspect ratios 1.5 and 2.7. These values are based on the total
wing span and area including the part blanketed by the fuselage.
The NACA 65-009 airfoil is the same as that used in the freely
falling body investigation of reference 3, although since the publi-
cation of reference 3 the subscript 1 has been deleted from the
designation. The sweepback angles were selected to give ratios of
free-stream velocity to velocity normal to the wing leading edge
of 1.000, 1.207, 1.414, and 1.621.
MODELS AND TESTS
The rocket-propelled, winged test bodies were constructed of
wood and were 5 inches in diameter and approximately 5 feet long.
The airfoils were of aspect ratios 1.5 and 2.7 and were swept back 00,
340, and 150. In addition, for the 1.5 aspect ratio, the airfoil
was tested with a swee-back of 520. The airfoils were mounted on
the fuselage at zero angle of attack so as to have the midsemispan
quarter-chord point at the same longitudinal station as the design
center of gravity and had neither twist, tapor, nor dihedral. The
constant-chord sections were always normal to the leading edge. The
fuselages were made hollow to accommodate the propulsion unit, a
standard 3.25-inch Mk7 aircraft rocket motor developing about
2200 pounds of thrust for 0.87 second at an ambient preignition
temperature of 690 F. The stabilizing fine were rotated 450 to the
plane of the wings to minimize the effect of the wing wake on the
tail. With the exception of the arrangement with 520 sweepback,
there were two models of each configuration testod. A line drawing
of the general body arrangement is shown as figure 1 and photographs
of the test bodies are presented in figures 2 to 4.
The experimental data were obtained by launching the test bodies
at an angle of 750 to the horizontal and determining its velocity
along the flight path by the use of OW Doppler radar (AN/TPS-5).
Photographs of the launcher and radar are shown in figures 5(a)
and 5(b), respectively. A typical curve of velocity against flight
time obtained from a radar record is given in figure 6. The drag
data were obtained by differentiating the part of the curve
corresponding to the time the bodies were coasting (after the
propellant had been expended) and converting the values of deceleration
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Alexander, Sidney R. & Katz, Ellis. Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds, report, February 24, 1947; (digital.library.unt.edu/ark:/67531/metadc58091/m1/3/: accessed January 21, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.