From Introduction: "V-g records supplied the NACA by the Bureau of Aeronautics in 1948 and 1949 have provided additional material. These records are analyzed statistically in this report to the frequency of large values of acceleration and airspeed, and results are compared with the design requirements."

Report presenting ram-recovery and mass-flow ratios for submerged inlets at four positions on the fuselage of a model of a hypothetical fighter airplane. Results related to the inlet location and effect of angle of attack are also provided.

"Results are presented of an investigation to determine the pressure distributions on a wing with leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip, an aspect ratio of 4.12, taper ratio of 0.36, and NACA 64A009 airfoil section. Tests were conducted at a Reynolds number of 3.5 x 10(exp 6) and a Mach number of 0.07 on the wing with and without 0.20 chord and 0.65 span split flaps deflected 60 degrees. These pressure distributions are analysed herein to determine the character of flow and its effect on the stability of the wing" (p. 1).

The following document describes x-ray diffraction measurements for an approximate crystal structure for the beta phase of metallic uranium.