PURPOSE: To reduce the aerodynamic drag for an airframe by fitting rectifying devices, which are brought into contact with the backward step of a missile at their front end sections, are extended backward in the air current direction perpendicularly to the face of the missile, and have the height higher than that of the step at their front sections, on the face of the missile.

CONSTITUTION: The rear section of a satellite fairing 1a is connected to a cylindrical lower fuselage 2 with a cross section area smaller than that of the satellite fairing 1a via a truncated conical lamp-shaped step 2 with a cross section area decreased toward the rear on the head section 1 of a rocket constituted of a conical front section 1b and the cylindrical satellite fairing 1a. Multiple plate-shaped rectifying devices 3 are protruded outward around the lower fuselage 2 at a uniform interval radially and perpendicularly to the plane of the fuselage 2 from the lower fuselage 2 in contact with the step 4 at their tips. The lateral flow of the peeling current with three-dimensional speed fluctuations by the boundary layer peeling of the air current generated behind the step 4 is suppressed, and the aerodynamic drag is reduced.