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National Advisory Committee for Aeronautics, Research Memorandum - A Wind Tunnel Investigation of Several Wingless Missile Configurations at Supersonic Speeds

A wind-tunnel investigation of several Wingless missile configurations
has been made. Lift, drag, and pitching-moment coefficients were measured
on a series of models at mach numbers of 2.EE to 3.35 and on one model from
1.76 to 5.05. In order to establish.a frame of reference with which to
evaluate the performance of the Wingless missile, results are also presented
for a conventional winged, cruciform missile.

The results of this investigation indicate that for the particular
center-of-gravity locations chosen, the maximum trimmed lift capabilities
of the Wingless configurations tested were, in general, somewhat less than
those of the winged missile. It is shown that a Wingless missile using
flared segments of the afterportion of the body to provide both stability
and control can have a lower drag in the trimmed condition than one using
an extendible section of the surface of the nose for control. This lower
drag is achieved with some sacrifice in maximum trimmed lift capability.
A comparison between Newtonian impact theory and experiment shows that
the experimental values of side-force and yawing—moment coefficients due
to lateral deflection of the tail control agree well with the theory at
angles of attack near zero. However, the experimental rolling-moment
coefficients and the side-force and yawing~moment coefficients at the
higher angles of attack.do not agree with the theory. The theoretical
values of pitching-moment coefficient due to deflection of the control
on the conical nose were in fair agreement with the experimental results,
whereas this comparison for the control behind the hemispherical nose was
poor.

In the short history of guided.antiaircraft missiles, airframe design
has proceeded along more or less conventional lines with relatively large
wings providing the forces necessary for maneuvering flight. For the
airborne missile, the use of large wings results in a rather high drag
associated with the stowage of the missile and a corresponding penalty
in the performance of the missile-carrying aircraft. The advantage of a
reduction in the size of the missile wings, from the standpoint of mini-
mizing this stowage drag, is obvious. Furthermore, if the wings could
be eliminated entirely and folding control and'stabilizing surfaces used,
the additional advantage of stowing and launching the missile from a tube
would be possible.‘5This-arrafigement would not only have a relatively low
stowage drag but should also reduce launching errors.