From summary: "The relative absorptions of X-rays by various substances are listed as a guide to the application of the X-ray photometric method in chemical analysis and to the estimation of interference by extraneous substances."

This report follows an investigation of a cargo truck found contaminated by various radioactive material on a routine trip from Arco, Idaho to the Hanford plant on May 8, 1952. The report analyzes the truck's route in an attempt to find the location of the contaminating region.

"The frequency of blade temperature to exhaust gas temperature is presented for two locations in the blade and at several operating conditions. The frequency response was determined by Fourier analysis of transient data. Two analytical methods are presented, and results are compared with experimental data. Dynamic response of turbine-blade temperature to exhaust-gas temperature exhibited the form of an approximate first-order lag" (p. 1).

Report presenting an investigation at Mach number 1.6 and a range of Reynolds number of the skin-friction drag and boundary-layer transition of a body of revolution. The body had a parabolic-arc profile, a blunt base, and a fineness ratio of 12.2 (NACA RM-10). Results regarding the effect of surface condition, drag breakdown, and results of boundary-layer surveys are provided.

Report presenting a flight investigation using rocket-powered models to determine some of the effects of wing-to-tail distance on the stability and control characteristics of a canard-missile configuration with 60 degree delta wings and control surfaces. Both models were tested over a range of Mach numbers from 0.8 to 2.0, and canard hinge moment and model drag data are presented. Testing indicated that additional fuselage length increases the lift-curve slope slightly and has very little effect on minimum drag.

Report presenting a flight investigation using four rocket-propelled models of low-aspect-ratio tailless configurations between Mach numbers 0.7 and 1.35. The configurations investigated were a 45 degree delta model with NACA 63A010 airfoil sections parallel to free stream, a 45 degree delta-wing model with NACA 63A006 airfoil sections parallel to free stream, a 37.5 degree swept-tapered wing model with NACA 64(sub 1)A012 sections perpendicular to quarter chord, and a 39 degree swept-tapered-wing model with NACA 64A006 airfoil sections perpendicular to quarter chord. Results regarding time histories, static longitudinal stability, dynamic longitudinal stability, order of oscillation frequency, rotational damping in pitch, and drag are provided.

Report presenting an investigation to determine the effects of turbine-blade coatings, supplied by fuel additives, on heat transfer with combustor exhaust gases to an S-816 alloy blade. Two fuel additives were used. The results indicated that the fuel additives provided an oxide coating on the combustor-liner wall and other metal parts, including the blade, exposed to the exhaust gas.

Report presenting wind-tunnel studies of the wake behind eight types of canard control surfaces of equal span mounted on a missile body at Mach number 1.93. The effect of simulated external rocket boosters on the pressure field was also determined for three control-surface plan forms. The investigation also included the effect of end plates attached to the tips of one of the controls surfaces.

Report presenting an investigation of some of the factors that affect autopilot systems in airplanes.

Report presenting an investigation at transonic speeds to determine the control characteristics of a linked tab and flap. The control device consisted of an auxiliary lifting surface (tab) mounted on the end of a boom which was linked to a full-span flap. The tab was found to be capable of reducing the flap hinge moment to zero through the angle of attack and Mach number range tested.

Friction and surface damage of several materials that are resistant to corrosion due to liquid metals was studied in air. The values of kinetic friction coefficient at low sliding velocities and photomicrographs of surface damage were obtained. Appreciable surface damage was evident for all materials tested. The friction coefficients for the combinations of steel, stainless steel, and monel sliding against steel, stainless steel, nickel, Iconel, and Nichrome ranged from 0.55 for the monel-Inconel combination to 0.97 for the stainless-steel-nickel combination; for steel, stainless steel, monel, and tungsten carbide against zirconium, the friction coefficient was approximately 0.47.

Theoretical performance for mixture of 36.3 percent liquid ammonia and 63.7 percent hydrazine with liquid oxygen bifluoride as rocket propellant was calculated on assumption of equilibrium composition during expansion for a wide range of fuel-oxidant and expansios ratios. Parameters included were specific impulse, combustion-chamber temperature, nozzle exit temperature, composition mean molecular weight, characteristic velocity, coefficient of thrust and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere, maximum specific impulse was 295.8 pound-seconds per pound. Five percent by weight of water in the hydrazine lowered specific impulse from about one to three units over a wide range of weight-percent fuel.

This report presents the results of an investigation conducted in the Langley free-flight tunnel to determine the effects of large artificial variations of several rotary lateral-stability derivatives on the dynamic lateral stability and control characteristics of a 45 degree sweptback-wing airplane model. Calculations of the period and damping of the lateral motions and of the response to roll and yaw disturbances were made for correlation with the experimental results. The calculated results were in qualitative agreement with the experimental results in predicting the general trends in flight characteristics produced by large changes in the stability derivatives, but in some cases the theory with the assumption of zero lag was not in good quantitative agreement with the experimental results.

Abstract: The yields of U²³⁷ and a fission product were measured as a function of maximum betatron energy, The ratio of the number of fissions divided by the number of U²³⁷ atoms increases with increasing maximum betatron energy. This is consistent with the picture that the higher-energy gammas leave the U²³⁷ atoms with enough excitation energy (above photofission and photoneutron thresholds) to also decay by fission or neutron emission. This secondary process increases the number of fissions and decreases the U²³⁷ yield, this increasing the above ratio.

The oxidation of uranium metal has been studied from the standpoint of the oxygen dependence of the reaction rate in an effort to establish the mechanism. The experimental data of Perkins agree with the theoretical dependence of the oxygen pressure derived this report. This agreement supports the hypothesis that the rate-controlling step in the migration of cations in the DO2 lattice, although the observed time dependence is not necessarily in agreement with this conclusion. Experimental entropies of activation are corrected for the observed pressure dependence. No firm conclusion could be reached as to whether the rate of diffusion or adsorption is rate-controlling.

The total neutron cross sections for normal uranium, U235, and Pu239 are reported as a continuous function of energy for neutron energies between 40 and 7500 Kev. Three additional measurements were made between 17 and 20 Mev. The data were obtained from a good geometry transmission experiment in which 1-in.-diameter cylindrical samples were interposed midway between a neutron source and a neutron counter spaced at about 20 in. separation. In general, the statistical errors were within +- 0.2 barn. Measurements on normal uranium were in agreement with those made at Wisconsin in 1950 (LA-1060). The total cross section curves are almost identical for the three materials and very similar to those of other heavy elements. This suggests that the total neutron cross section for other heavy elements can be predicted with some accuracy.

Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of an external store on the lift, drag, and pitching-moment characteristics of an unswept wing of aspect ratio 4 at Mach numbers of 1.41, 1.62, and 1.96.

Memorandum presenting the effects of rivets and lap joints on the drag of bodies at zero lift at supersonic Mach numbers to 2.1 in free flight with rocket-propelled models. Four forward-facing lap joints 0.064 inch high, four similar lap joints facing rearward, and four double rows of 1/8-inch-diameter brazier head rivets were tested on a 5-inch-diameter body 56 inches long.