Aerodynamic characteristics at a Mach Number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls Page: 4 of 21
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NACA RM L58D24 E . : *
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free-stream dynamic pressure
cross-sectional area of cylindrical section of body
diameter of cylindrical section of body
angle of attack of body center line, deg
deflection of all-movable controls with respect to body cen-
ter line, positive when trailing edge is down or left, deg
deflection of trailing-edge flap with respect to body center
line, positive when trailing edge is down or left, deg
lift-drag ratio, CL/CD
longitudinal distance rearward of nose, in.
MODELS AND APPARATUS
Sketches of the models are shown in figure 1.
acteristics of the models are given in table I, and
the forebody are given in table II.
The geometric char-
the coordinates of
The model had a body consisting of a 5-caliber forebody with a
round nose followed by a straight tapered section that fairs into a
5-caliber cylindrical afterbody. The fins, trailing-edge flaps, and
all-movable controls were flat plates with rounded leading edges and
blunt trailing edges.
The cruciform-fin configuration consisted of the body, cruciform
fins having a 5 apex angle, and cruciform trailing-edge flaps in the
plane of the fins (fig. 1). An 0.033-caliber gap separated the fins
and flaps. The hinge line of the flaps was at the 93.3-percent body
station and the 33.5-percent chord line of the flaps.
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Robinson, Ross B. & Bernot, Peter T. Aerodynamic characteristics at a Mach Number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls, report, August 4, 1958; (digital.library.unt.edu/ark:/67531/metadc53265/m1/4/: accessed September 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.