Abstract:
Measurements of lift, drag and pitching moment have
been made in the. No. lA Wind Tunnel at the College of Aeronautics
at a speed of 132 f.p.s. on a model rocket supplied by the
Armament Research Establishment, Woolwich. The model was
tested with three different tail spans, and with no tail.
The tests made showed that the increase in static
stability was almost directly proportional to the net span of
the tail fins. For small angles of incidence the fin effectiveness
was the same for the fins mounted vertically and horizontally,
and for the fin assembly rotated through 45°. The model vas
found to be statically stable about its point of suspension for
all three fin sizes, and no unsatisfactory characteristics were
Observed over the test range of incidence from -12° to +18°.
The experimental results have been compared with
estimates based on slender body theory.
