Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.

Memorandum presenting tests in the 9-inch supersonic tunnel to investigate the factors that determine the magnitude of the wing-tail interference effects on the static longitudinal stability of supersonic missile configurations with low-aspect-ratio, tandem, cruciform lifting surfaces and to develop a missile configuration with a minimum variation in static margin due to wing-tail interference effects.

Report presenting boundary-layer measurements on rocket-powered free-flight models to determine average skin-friction coefficients. The test body, NACA RM-10, was a fin-stabilized parabolic body of revolution of fineness ratio 12.2 with a blunt base to provide space for a rocket jet. Results regarding the skin-friction and boundary-layer profiles and experimental and theoretical curves are provided.

Memorandum presenting lift, drag, and pitching-moment data and some static rolling-moment data are presented for missile configurations having wing-tail-span ratios equal to and less than 1. The configurations include variations in wing and tail plan forms, wing-tail-span ratios, body length, and nose shape.

Report presenting the effects of a low-speed wind-tunnel investigation to determine the effects of vertical-fin location and area on the static and rotary lateral stability characteristics of semitailless airplane models. Results regarding straight flow, yawing flow, and rolling flow are provided.

Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.

Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.

This study was made to evaluate the effects of several operatin variables on the yield at the reduction step in motel fabrication. The original question was whether or not the addition of recycled metal to the charge had an effect on the yield. To circumvent possible masking of such as effect by changes in other operating factors, simultaneous data on the weight of Pu in the powder charge, the % conversion of the powder to PuF{sub 4} in the fluorination step, the firing time, and the maximum temperature were also studied. This permitted estimation of the separate effects of al five factors. The period covered by the data was October through December, 1950.

This document contains reproductions of technical papers on some of the most recent research results on aircraft structures from the NACA Laboratories. These papers were presented by members of the staff of the NACA Laboratories at the NACA conference held at the Langley Aeronautical Laboratory March 7, 1951. The purpose of this conference was to convey to those involved in the study of aircraft structures these recent research results and to provide those attending an opportunity for discussion of these results.