From Introduction: "This paper presents the basic design method and experimental results of calibration of a nozzle which was constructed to conform to the analytically determined ordinates."

From Introduction: "The purpose of this report is to treat analytically heat addition heat addition to a divergent stream with initially sonic flow and to employ the results thus obtained in evaluating the effect of delayed combustion on convergent-divergent nozzle performance."

"An approximate method for computing water loads and pressure distributions on lightly loaded elliptical cylinders during oblique water impacts is presented. The method is of special interest for the case of emergency water landings of helicopters. This method makes use of theory developed and checked for landing impacts of seaplanes having bottom cross sections of V and scalloped contours. An illustrative example is given to show typical results obtained from the use of the proposed method of computation" (p. 1).

Report presenting an experimental investigation to determine the effect of changes in shape of the rear fuselage of an airplane on ditching behavior. The behavior of the models was recorded with a high-speed camera, the records were analyzed, and the data is presented as curves of speed, attitude, and center-of-gravity height plotted against time.

Note presenting results of an investigation of the fatigue strength of several full-scale aircraft wing structures. The 34 fatigue failures which resulted from the tests were of four main types and occurred in three principal localities on the test wings. Results regarding the definition of fatigue failure, load history of specimens, description of fatigue failures, spread in fatigue life, stress concentration factors, rate of crack growth, and effect of fatigue damage on natural frequency and damping are provided.

From Summary: "The general effect of wing sweep on cloud-droplet trajectories about swept wings of high aspect ratio moving at subsonic speeds is discussed. A method of computing droplet trajectories about yawed cylinders and swept wings is presented, and illustrative droplet trajectories are computed. A method of extending two-dimensional calculations of droplet impingement on nonswept wings to swept wings is presented."

Report presenting an analysis for optimum controllers of general, linear, time-invariant multiloop systems. General representations of controller characteristics, stable process characteristics, and error relations are used. General solutions are presented for four special cases.

Note presenting a method for the rapid determination of design velocity diagrams of turbine stages within specified aerodynamic limits. The method is presented in both chart and tabular form.

Note presenting porcelain-enamel ground coats, which were prepared and applied under conditions that gave various degrees of adherence between enamel and a low-carbon steel. This study was primarily undertaken to find out additional information on the mechanism of adherence of porcelain-enamel ground coats to iron.

"A study of the motion of a personal-owner or liaison airplane through the stall and into the incipient spin has been made by catapulting a dynamic model into still air. The results showed that the model became unstalled in inverted flight after its initial rotation of substantially 180 degrees in roll. Since the rates of rotation were low, it may be inferred that termination of the incipient spin would be most readily obtained by proper control movements at this point" (p. 1).

Presents zero-lift drag data of an NACA RM-10 slender body of revolution with and without stabilizing fins attached. The results from several wind tunnels and in flight are compared. The results cover a Reynolds number range from about 1 time 10 to the 6th power to 40 times 10 to the 6th power for the flight models. The Mach numbers covered include 1.5 to 2.4 in the wind tunnels and 0.85 to 2.5 in flight.