High Angle of Attack Missile Aerodynamics at Mach Numbers 0.30 to 1.5

Abstract : A large body of wind tunnel data was generated by tests of a smooth missile model with several interchangeable nose parts. The tests were conducted at subsonic through supersonic speeds at angles of attack from 0 to 180 degrees. They were part of the FDL and SAMSO technology studies which preceded design of the MX missile. Measurements of both surface pressures and total forces and moments were made at a variety of Mach numbers and Reynolds number combinations. This data was supplemented with wake flow-field measurements of the impact pressure and flow direction at angles of attack where maximum induced side force was expected to occur. A review of the literature for subsonic and transonic aerodynamic characteristics of bodies of revolution was conducted. A comprehensive discussion is provided of the important variables of the high angle of attack flow phenomena. The test data provided insight into the effect of several variables that had not been adequately treated in the past. The high angle of attack data was analyzed to deduce the vortex shedding location, the vortex strength, and the vortex paths in the wake. Discrete vortex theory was examined as a method which could be modified, based on experimental data, and used to predict the aerodynamic characteristics of missiles to greater accuracy. An alternate approach to developing a prediction method was explored by means of a correlation of the surface pressure data.