Report presents the results of an investigation conducted to study the effects of the inert gases, argon and helium, upon flame speed and expansion ratio in exploding mixtures of carbon monoxide, oxygen and water. For the particular gas mixtures investigated the results show that: (1) With the possible exception of helium in small amounts the addition of inert gas always produces decreased flame speed and expansion ratio; (2) like volumes of argon and helium have very different effects upon flame speed but practically the same effect upon expansion ratio; and (3) the difference in the effect of these two gases upon speed is independent of the ratio of carbon monoxide to oxygen. A discussion of some possible modes by which inert gases may produce the observed effects is included.

From Introduction: "Performance results of the tail-pipe burning investigation on the TG-180 turbojet engine and a comparison of experimental results with theoretical calculations are presented."

A 1/5.5-size powered dynamic model of the Columbia XJL-1 amphibian was landed in Langley tank no. 1 in smooth water and in oncoming waves of heights from 2.1 feet to 6.4 feet (full-size) and lengths from 50 feet to 264 feet (full-size). The motions and the vertical accelerations of the model were continuously recorded. The greatest vertical acceleration measured during the smooth-water landings was 3.1g.

From Introduction: "This report presents an analysis based on flight and wind-tunnel test data directed toward the determination of the probable cause of the pitch-up. Wing pressure distribution and stability and control characteristics in the dive are also included."

Report of testing on an untapered 35-degree sweptback airfoil-flap model, representative of a wing or tail surface, with several 1/4-chord full-span flaps differing in aerodynamic balance. A plain flap, a horn-balanced flap, and a beveled-trailing-edge flap were compared to a flap that had a 31-percent-flap-chord overhang balance. Information about lift, pitching-moment, and hinge-moment characteristics is provided.

Report presenting a comparison of the calculated response characteristics corresponding to the maximum maneuver of a variable-incidence, a canard, and a conventional tail-aft-control, beam-rider, guided missile. All the configurations were designed to be the same except for the effects of changes in lift ratio. Results regarding limited control-surface deflection, limited angle of attack of the critical surface, servo energy, surface-deflection interference, and size of surfaces are provided.

Report presenting an investigation at low speed in the low-turbulence tunnel to determine the effects of variations in propeller-shank geometry and propeller-spinner-juncture configuration on the aerodynamic characteristics of an NACA 1-series cowling-spinner combination with an eight-blade dual-rotation propeller. Results regarding internal flow and external flow are provided.

Report presenting an investigation to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing wing thickness while external braces were used to provide the necessary bending strength. The investigation was conducted with two rocket models of aspect ratio 3.04, and unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data was compared to a previous study involving a model with a thicker cantilever wing.

Report presenting an investigation to determine the effects of compressibility on the hovering performance and the blade pitching moments of a helicopter rotor with a tip airfoil, a root airfoil, and twist. Results regarding hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.

Memorandum presenting a model of a 60 degree delta-wing bomber with strut-mounted Siamese nacelles, which was designed, with the use of a symmetrical fuselage indentation, to have a smooth average area distribution at a Mach number of 1.20. The results show that the configuration drag rise was significantly higher than that from the equivalent-body tests and area-rule theory throughout the Mach number range. Results regarding total drag and pressure drag are provided.

Report discussing pressure distributions on a thin conical cambered low-aspect-ratio delta wing over a range of Mach numbers. Combinations tested included the wing in combination with a basic Sears-Haack body and a body indented symmetrically for Mach number 1.2. Results regarding wing pressure distributions, effects of body indentation on the wing pressure, body pressure distributions, and effects of body indentation on body pressures are presented.

Report presenting an investigation to determine the effects of spanwise and chordwise external store location on the aerodynamic characteristics of a cambered 45 degree sweptback wing-body configuration at a range of Mach numbers. Information about the drag characteristics of the various configurations, lift characteristics, and longitudinal stability characteristics is presented.