"The manner in which flow in a boundary layer becomes turbulent was investigated on a flat plate at wind speeds generally below 100 feet per second. Hot-wire techniques were used, and many of the results are derived from oscillograms of velocity fluctuations in the transition region. Following a presentation of the more familiar aspects of transition, there are presented the very revealing facts discovered while studying the characteristics of artificially produced turbulent spots" (p. 853).

Memorandum presenting two right circular cylinders tested in axial free flight over a Mach number range of 0.4 to 1.7 by using the rocket-boosted-model technique. Results regarding time history, basic data cross plots, center of pressure, and drag are provided.

An investigation was made of the spray characteristics of a jet-powered dynamic model of the Bureau of Aeronautics DR 56 flying-boat design with a vee tail. A limited investigation was made to determine the effect of the change in tail design on the take-off and landing behavior in smooth water and in waves 8 feet high (full size).

Report presenting the low-speed longitudinal stability characteristics of a wing with 45 degrees of sweepback of the quarter-chord line, an aspect ratio of 8, a taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections parallel to the air streams investigated in the 19-foot pressure tunnel. Results regarding the basic wing, wing with fences, wing with trailing-edge flaps, wing with leading-edge flaps, a combination of both flaps, fences with the flaps deflected, leading-edge roughness, and the wing-fuselage combustion are provided.

From Introduction: "The data presented herein include the standard engine performance parameters of net thrust, specific fuel consumption, and engine total-pressure ratio that reflect the performance available from the use of pentaborane as a fuel. The influence of the boric oxide deposits from the high-concentration pentaborane fuels on engine component performance is presented."

Report presenting an analysis to evaluate the effectiveness of supplying secondary airflow for an ejector exhaust nozzle by bypassing from the main inlet. If optimum weight flow is maintained, the performance of the system is about the same as for ejectors supplied by fixed auxiliary inlets up to Mach number 3.0.

Memorandum describing the blades of the tapered-tip 0.4 hub-tip diameter ratio transonic rotor, which were reset 7.5 degrees in the rotor disk and twisted from 0 degrees at the mean-radius section to 4.5 degrees at the tip to increase the specific weight flow approximately 10 percent to 36.3 pounds per second per square foot of frontal area. Results regarding the rotor overall performance, rotor flow parameters, comparison of blade-element performance and design rules, and minimum-loss and choking incidence-angle analysis at rotor hub section are provided.

The dynamic characteristics of turbojet engine with variable exhaust nozzle area were investigated over a range of altitudes and flight Mach numbers. These characteristics generalize to standard static level condition. Data resulting from approximate step disturbances in either manipulated variable suggested functional relationships from which functions can be derived. The constants of the transfer functions are listed for five combinations of engine speed and exhaust nozzle area. The minimum data needed to completely define the transfer functions were: experimentally determined dynamic characteristics, such as engine time constant and initial rise ratio, resulting from either manipulated variable; static characteristics determined from steady-state performance curves.

Memorandum presenting an experimental investigation of four rectangular-throat two-dimensional wedge exhaust nozzles. Three of the nozzles were designed to conform to Prandtl-Meyer streamlines for pressure ratios of 5, 10, and 24, and a fourth, arbitrarily contoured, with a length less than that required for isentropic expansion, was designed for a pressure ratio of about 9.