Memorandum presenting a comparison between the time history of skin temperature measured on the nose of a V-2 and the temperature computed using Eber's experimental relation for heat-transfer coefficients for conical bodies under supersonic conditions. A general method developed for making skin-temperature calculations is used to compute the variation of skin temperature with time for a wide range of values of the pertinent parameters. Results regarding the validity of skin-temperature calculations, ranges of skin temperature, and skin temperatures for a typical supersonic airplane are provided.

Report presenting testing on the first of a series of flutter rockets, designated the NACA FR-1-A, which was tested with two identical swept wings. Results regarding the launching, flight, and wing failure are provided.

Memorandum presenting an investigation in the free-flight tunnel to determine the effect of the sloshing of fuel in partly filled, unbaffled tanks on the lateral stability of a free-flying model. Flight tests were made to determine the effects of the water sloshing for different depths of water and various masses and moments of inertia of the model. The sloshing caused small-amplitude, high-frequency lateral oscillations which were superimposed on the normal Dutch roll oscillation so that the lateral motions of the model appeared jerky.

Report presenting a wing-tunnel investigation in straight and pitching flow to determine the effects of independently varying aspect ratio and angle of sweep on the longitudinal rotary stability characteristics of a series of ten untapered wings. The investigation showed that an interdependent relationship existed between the effects of aspect ratio and sweep. Results regarding pitching moment due to pitching velocity and lift due to pitching velocity are provided.

An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably well with full-scale flight results.

From Introduction: "An analytical method for estimating turbine performance from the blade angle8 and flow areas was therefore developed at the NACA Lewis laboratory and is described herein."

An investigation conducted in the icing research tunnel on a ramp type recessed fuel cell vent assembly to determine its aerodynamic, rain, and icing characteristics. Although the vent-tube openings are located in the region of maximum ramp pressure, vent-tube static pressures are marginal for a low flight speed.

Report presenting the results of pressure-distribution measurements obtained in flight over the free-blown canopy of a fighter-type airplane. The measurements were compared to those of the same canopy in wind-tunnel testing to determine the degree of correlation and effects of Mach number and distortion on the pressure distribution.

From Introduction: "An analytical method for estimating turbine performance from angles and flow areas was therefore developed at the NACA Lewis laboratory in 1947 and is described herein."

From note: "Report discussing the history of the research of potassium 40 and its radioactivity, as well as the author's own investigations into the isotope."

"Data obtained in tests of a 10-foot diameter, three-blade propeller, having NACA 10-(3)(08)-03 blades, conducted in the Langley 16-foot high-speed tunnel are presented. The propeller performance quantities related by the tests are thrust, torque, efficiency, and advance ratio for various rotational speeds or stream Mach numbers with blade angle as a parameter. Advance Mach numbers varied from 0.12 to 0.64" (p. 1).

"This paper presents the results of flight tests to determine the lateral and directional stability and control characteristics of the Grumman F8F-1 airplane with three vertical-tail configurations. The data presented herein have no bearing on the performance characteristics of the airplane, which were not measured but which were considered to be exceptionally good. The conclusions reached regarding the lateral and directional stability and control characteristics are summarized in this report" (p. 1).