Effects of free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing fighter airplane model at a Mach number of 2.01 Page: 2 of 32

                                
NASA Technical Lib
NACA RM L55BO1         .      3 1176 01437 7585  '
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM                       -.
EFFECTS OF FREE-FLIGHT ROCKET-MMODEL BOOSTER-ADAPTE,
CONFIGURATIONS ON THE AERODYNAMIC CHARACTERISTICS C      ,    t
C)     .     ot  0
IN PITCH AND SIDESLIP OF A SWEPT-WING FIGHTER
AIRPLANE MODEL AT A MACH NUMBER OF 2.01    UC             O
By Ross B. Robinson                        ,,
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Results are presented of a wind-tunnel investigation to determine
the effects of various free-flight rocket-model booster-adapter config-
urations on the aerodynamic characteristics in pitch and sideslip of a
swept-wing, fighter airplane model for a Mach number of 2.01. The model
alone and in the presence of various booster-adapter configurations was
tested through an angle-of-attack range from -2o to 110 and through a
sideslip range from 00 to 130. Normal-force, lateral-force, pitching-
moment, and yawing-moment coefficients of the airplane model were meas-
ured, and schlieren photographs of the various configurations were
obtained.
The results of this investigation indicate that the revised adapter
configuration should substantially reduce the pitching moment of the
model at separation provided the drag flap on the booster is moved
rearward.
The model alone has adequate longitudinal and directional stability
and should trim at a small positive angle of attack with zero incidence
of the horizontal tail.
INTRODUCTION
One of the problems in the development of rocket-boosted free-flight
test vehicles is to minimize the interference effects of the booster
adapter on the model. The problem is complicated by mechanical require-
ments, which often necessitate the use of asymmetric or bluff adapter
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