From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."

Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.

Memorandum presenting an experimental investigation conducted at Mach numbers 1.5, 1.8, and 2.0 to determine the effects of several throat boundary-layer bleed configurations on the performance of a 25 degree half-conical side-inlet system. The effects of several flush-slot configurations and a porous-surface bleed were determined over ranges of angle of attack and bleed-duct and main-duct mass flow.

Report presenting an investigation of the effects of changing indentation design Mach number on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination designed for high performance at a range of Mach numbers. Theoretical results of zero-lift wave drag for the wing-body combination agreed well with the experimental data. Results regarding the bodies, systematic series of wing-body combinations, -2 degree angle of incidence, M = 1.4 revised body, and transition are presented.