Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From Page: 4 of 36
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2 . . ." . ." . . " 0" * *00 0
NACA RM LS1I28 : i :. :. : .*:. :... :* 3
iw average wing incidence for three wings measured in plane
parallel to the direction of flight, positive when tending
to produce clockwise roll as seen from the rear, degrees
0 angle of twist due to m, radians
h/c spoiler extension above wing surface in local chord lengths
p/Pzg wing bending-stiffness parameter, inches per pound
9/m wing torsional-stiffness parameter, radians per inch-pound
pb/2V wing tip helix angle, radians
cmgla effective section twisting-moment coefficient per unit rolling
CDT total drag coefficients
a at altitude of test
o at sea level
r at reference station (mid-control)
6 per degree of aileron deflection
MODELS AND TECHNIQUE
The geometric characteristics of the test vehicles used in this
investigation are described in the sketches and photographs of figures 1
The airfoil sections used on the configurations tested were the
NACA 0009-1.16 38/1.14 (modified) at the root and the NACA 0007-1.16
38/1.14 (modified) at the tip. The aspect ratio b2/S2 for all models
tested was 3.02. Both wings of the proposed airplane are equipped with
upper-surface spoilers and boundary-layer control fences, lower-surface
tip skids, and plain partial-span trailidg-edge ailerons. During most
rolling maneuvers, an unsymmetric condition occurs which could not be
duplicated with a single three-wing test vehicle of the present type,
so several models were flown to test the airplane right and left wing
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Strass, H. Kurt & Marley, Edward T. Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From, report, February 25, 1952; (digital.library.unt.edu/ark:/67531/metadc52895/m1/4/: accessed January 16, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.