The side thruster is a highly responsive means for attitude control of miss
iles. The sidejet force is influenced by the interaction of the sidejet wit
h the external airflow. The sidejet aerodynamic interaction effects were an
alyzed from following two viewpoints: 1) the pressure field in the vicinity
of the sidejet and 2) the Force acting on the missile. Technical data of s
idejet aerodynamic interaction effects were obtained by means of Right test
s of missiles that were equipped with four impulse side thrusters that were
small-size, rapidly burning solid-propellant rocket motors. The data agree
with computational fluid dynamics analyses and wind-tunnel tests.