Report presenting a correlation of carbon deposition of 19 fuels in a turbojet combustor as a function of the boiling point and of the flame height at the sooting point of the fuels in a simple wick lamp for a particular combustor operating at a single set of conditions. Two similar investigations with different combustors, operating conditions, and nine different fuels yielded similar correlations on the same graph.

Report discussing an investigation of a parabolic body of revolution with and without the effects of an annular jet exhausting from the base. The aerodynamic characteristics, pressures, lift-curve slope, and other characteristics with the jet in operation and inoperative were compared.

Report presenting an investigation to evaluate the engine service performance of nozzle-diaphragm blades of AISI 321 and AISI 347 stainless steels. Data were obtained from three nozzle diaphragms alternately bladed with each of the two materials. Results regarding a visual inspection, a metallurgical examination, the mechanism of cracking, and the classification of failures are provided.

Report presenting the results of tests of four model wings of aspect ratios 1, 2, 4, and 6 and with NACA 65(sub 1)-210 sections. The experimental lift-curve slope is compared with predictions from theory. Results regarding lift, drag, and pitching moment, lift-curve slope, drag divergence, minimum drag, and pitching moment are provided.

Memorandum presenting a method for approximately determining the minimum moment of inertia of an arbitrarily shaped area, such as the section of a hollow turbine blade. The practical application of the method involves a simple routine tabular procedure.

Report presenting the aerodynamic characteristics of an all-movable, triangular-plan-form wing alone and with a body as determined from semispan model tests. The agreement between calculated and experimental results was not satisfactory for the most part, which seemed to be due to the failure of linear theory to define the actual flow field about the configurations investigated. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

From Introduction: "Tests have recently been conducted in the Langley 8-foot high-speed tunnel (reference 1) to study the effects of changes in operating advance ratio, blade plan form, blade-section thickness, section camber, and other variables on the on the propeller characteristics in the transonic-speed range. The method in reference 2, which evaluated the profile drag losses and the induced losses seperately, is followed in this paper. The method as presented offers the general prediction of propeller performance, and can be used to supplement the experimental data."

Report presenting an investigation to determine the temperature and pressure distributions in the jets issuing from two parallel nozzles of a turbojet engine located close together and impinging on the ground at an angle of 20 degrees. Results regarding the jet-nozzle pressure ratio, constant-temperature parameters, and temperature contours are provided.

From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."

An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel.

Report presenting a temperature survey made in the wake of two closely located parallel jets emerging into the atmosphere from two types of twin convergent nozzles. Results regarding the twin unshrouded nozzles and twin nozzles with twin geometry-simulated shrouds are provided.

Memorandum presenting the low-speed lateral control characteristics of a 32 degree sweptforward wing of aspect ratio 5.8 and NACA 65-series airfoil sections as determined in the 19-foot pressure tunnel. The investigation include the measurement of the hinge-moment and normal-force characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and several configurations of spoilers.

Report discussing an investigation of the longitudinal trim and drag characteristics of two airplane configurations through the transonic speed range. One configuration had a thin straight wing and tail and one had a thicker 35 degree sweptback wing and a 46 degree sweptback tail on the same fuselage-fin arrangement. Information about the control effectiveness and stability and application to a full-scale airplane is also provided.

A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.

Report presenting an investigation of the time lag between flap deflection and force development on a rectangular wing with a 9-percent-thick symmetrical circular-arc profile with a full-span 30-percent-chord flap. This was performed in order to determine further information about the rapidity of response for a supersonic missile after a given flap deflection due to the potential time lag between the deflection of the controls surfaces and the development of aerodynamic forces.

Report presenting the planing characteristics for six surfaces representative of hydro-ski forms as determined by tank tests.Testing was made at specified trims, speeds, and sufficient loads to define variations with wetted length. Data from the testing is provided in the form of plots of wetted length, load, resistance, trimming moment, and draft against wetted area.

Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.

From Summary: "A method is given for determining the horizontal tail loads in maneuvering flight. The method is based upon the assignment of a load-factor variation with time and the determination of a minimum time to reach peak load factor. The tail load is separated into various components. Examination of these components indicated that one of the components was so small that it could be neglected for most conventional airplanes; therefore, the number of aerodynamic parameters needed in this computation of tail loads was reduced to a minimum. In order to illustrate the method, as well as to show the effect of the main variables, a number of examples are given. Some discussion is given regarding the determination of maximum tail loads, maximum pitching accelerations, and maximum pitching velocities obtainable."

Declassified 23 Nov 1973. It is assumed that the Grand Coulee Dam would be destroyed by one direct hit following detonation of an atomic bomb. Major effects of the explosion include flooding and isolation of Richland, flooding of Midway Substation, and flooding of surrounding areas. Maximum water elevations following a direct hit and indirect hits are estimated. Data are presented for flow through openings and flow through dam failure. (HLW)

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Report discussing progress made on geologic studies under the Colorado Plateau Project. The geologic studies that were in progress during the time of this report consist of the following: "(1) General geologic mapping in southwestern Colorado and southeastern Utah. (2) Regional stratigraphic and sedimentary studies in Colorado, New Mexico, Utah, and Arizona. (3) Studies of past and present ground-water conditions in southwestern Colorado and southeastern Utah."

Report discussing a geological experiment in which 48 drill holes in the Calamity area were logged with the objective to check the results obtained in a previously done experiment by the Schlumberger Well Surveying Corporation.

The following report summarizes the results of a brief geological examination made by the Geological Survey of the small uranium deposit in the Majuba Hill mine, Pershing County, Nevada.