A force investigation of a supersonic aircraft configuration and various combinations of its components has been conducted in the Langley 4- by 4-foot supersonic tunnel. The tests were performed at Mach numbers of 1.40 and 1.59 at a Reynolds number of approximately 600,000 based on the wing mean aerodynamic chord and are a part of an extensive investigation of the force and pressure-distribution characteristics of this configuration.

An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61 to determine the stability of control characteristics of a supersonic aircraft configuration with a 40 percent sweptback wing and equipped with spoiler lateral control devices. Some effects of various types of spoilers, spoiler span, projection, and chordwise location were investigated, as well as the hinge-moment characteristics for a plain spoiler.