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National Advisory Committee for Aeronautics, Research Memorandum - Preliminary Investigation of the Drag Characteristics of the NACA RM-10 Missile at Mach Numbers of 1.40 and 1.59 in the Langley 4x4 Foot Supersonic Tunnel

A parabolic body of revolution (0.287escale model of_the NACA'RM-lo)
has been tested in the Langley 4- by h-foot supersonic tunnel at Mach
numbers of l.h0 and 1.59, and at Reynolds numbers based on body length
varying from 1.8 X 106 to 4.7 X 106. The effects of Reynolds number,
fins, internal contour of body base, and two support systems on body
pressure and force drag were investigated at an angle of attack of 0°.

Laminar flow existed over the entire length of the sting-supported
body (without fins). Addition of a transition strip at the maximum body
diameter produced turbulent flow over the rear part of the body but did
not-significantly affect the forebody pressure distribution. The base
pressure, howaver, was more negative than that produced by a corresponding
laminar flow. When the fins were added to the body the base pressure
became more negative_than on the body without fins and was independent of
the type of boundary layer existing ahead of the fins. Fin interference
effects on the forebody pressure drag were small.

Varying the internal contour of the model base had no significant
effect on the base pressure.

The use of a central wire-support system extending ahead of the body
produced a turbulent flow over the entire body but did not significantly
affect the forebody pressure distribution.

In an attempt to evaluate stale effectxon slender bodies, the
National Advisory Committee for Aeronautics-has undertaken a coordinated
research program to test a parabolic body of revolution having a fine-1’
ness ratio of 12. 2 (NACA RM- 10 missile). Various scale models of this
missile have been tested in NACA supersonic wind tunnels (references 1
to h) and rocket—propelled models have be_en tested __in _flight_ (refer—
ences 5 to 7). The data obtained in these tests cover a wide range
of Reynolds numbers and, at“& given Mach numher, data are available_for
a range of Reynolds number. In general, this attempt to evaluate the
scale effect has been limited to the analysis of the drag coefficient
at an angle of attack of 0°.