EXPERIMENTAL INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF AN AIR-TO-AIR MISSILE EMPLOYING CRUCIFORM WINGS AND TAIL OF RECTANGULAR PLAN FORM AT MACH NUMBERS OF 1.4 AND 1.9

摘要

The aerodynamic characteristics of a model of an air-to-air missile employing variable-incidence cruciform wings of rectangular plan form and a fixed cruciform tail of rectangular plan form, and the characteristics of its body-wing and body-tail components, as determined from a wind-tunnel investigation for Mach numbers of 1.4 and 1.9, are presented. The results include normal-force, pitching-moment, and axial-force data for the body-wing-tail, body-wing, and body-tail combinations, and normalforce, hinge-moment, and axial-force data for the individual wing panels. The investigation was conducted at a constant Reynolds number of 1.51 million based on the wing chord. All the results are presented in coefficient form plotted against angle of attack. No discussion of the results is included.