From Summary: "Curves are presented that show the theoretical performance of the augmentation method for various amounts of water injected and the effects of varying flight Mach number, altitude, ambient-air temperature, ambient relative humidity, compressor pressure ratio, and inlet-diffuser efficiency. Numerical examples, illustrating the use of the psychrometric chart and the Mollier diagram in calculating both compressor-inlet and compressor-outlet conditions when water is injected at the compressor inlet, are presented."

Report presenting a theoretical treatment of absorption problems that considers the following cases: radiation is normal to an absorber with plane parallel surfaces, radiations are of several polyenergetic types, induced radioactive isotopes decay to stable atoms in multistep decay processes, and radiations from the absorber affect the time-dependency of the source activity. Radiation from intermediate isotopes can become more dangerous than the original activity, so the entire range of radiations must be accounted for.

Report presenting a critical comparison between experimental and theoretical results for the aerodynamic characteristics of wings at supersonic flight speeds. The lift, pitching moment, and drag characteristics of several families of wings of varying plan form and section in the wind tunnel and compared with values predicted by the three-dimensional linear theory.

Note presenting a practical method, employing a lofting technique, for determining the profile coordinates of an air inlet for the leading edge of an airfoil from formulas which are dependent only on the airfoil coordinates and on the height of the opening. It was found that the base-profile concept of thin-airfoil theory could be applied to a ducted airfoil with satisfactory results. Results regarding design inlets, modified inlets, and end-closure shape are provided.

Report presenting wind-tunnel testing to determine the temperature-recovery factors for laminar, transitional, and turbulent boundary layers on a flat plate.

Report presenting the vibration characteristics of several symmetrical ball-root-type blades simulating the mass and natural frequency of axial-flow-compressor blades under various mounting conditions by subjecting them to controlled periodic excitation and centrifugal loading. Results regarding loose single ball-root mounting, loose-lubricated, single ball-root mounting, double ball-root mounting, and damping measurements are provided.

Report presenting testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.

Report presenting an experimental and analytical investigation to determine the effect of humidity on turbojet-engine performance. The humidity effect was found to be very small with the magnitude depending on the basis of comparison. Results regarding the calculated humidity correction factors, experimental effect of humidity of engine performance, and variation of saturation specific humidity with altitude are provided.

This document presents equations for the two-dimensional stationary problem of gas dynamics, and uses them to derive other equations, including equations for vorticity.

An investigation was made to determine the effects of vertical-tail size and length and of fuselage shape and length on the static lateral stability characteristics of a model with wing and vertical tails having the quarter-chord lines swept back 45 degrees. The results indicate that the directional instability of the various isolated fuselages was about two-thirds as large as that predicted by classical theory.

Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.

From Summary: "The dynamic characteristics of an axial-piston, variable-stroke, jet-engine fuel pump were experimentally determined by frequency-response tests. It was found that the pump can be approximated by a first-order linear system with an average time constant of 0.04 second. The order of magnitude of the lag of the pump is negligible compared with current jet engines. It was also established that such a pump may be used for obtaining sinusoidal fuel pressures of variable frequency and amplitude."

Report presenting an approximation process that can be used to determine both composition and temperature resulting from a chemical reaction. It is suitable for use with any set of reactants over the complete range of mixture ratios as long as the products of reaction are ideal gases.

A method is described by means of which the laminar friction layer at a wall with arbitrary pressure distribution may be calculated from Prandtl's boundary-layer equations.

Report presenting testing of two water-cooled turbines, one of aluminum alloy using forced-convection cooling and one of stainless steel using natural-convection cooling, to obtain heat-transfer and general operating data like blade temperatures, coolant-flow rates, and coolant pumping losses. Results regarding outside and inside heat-transfer results, coolant pumping power, general operating results, and practical considerations for both are provided.

Report presenting an investigation of the laminar boundary layer on a flat plate in a supersonic stream by means of a Zehnder-Mach interferometer and a total-pressure probe. Results regarding the velocity and density profiles, skin friction, and recovery factor are provided.

Report presenting a performance investigation of an optical torquemeter, which has an indicating system that requires no physical connection to the torsion shaft. Dynamic tests of the torquemeter were made over a range of shaft speeds and torque loads. Results regarding the torsion-shaft static calibration, dynamic operation, and practicability of the instrument are provided.

"An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel to determine the static lateral stability characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results of the investigation indicated high directional stability that decreased with increasing Mach number and positive effective dihedral that was essentially invariant with lift coefficient and Mach number" (p. 1).

Report presenting an investigation in the 4- by 4-foot supersonic tunnel to determine the static longitudinal stability and control characteristics of a supersonic aircraft configuration at a Mach number of 1.59. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line.

Note presenting an experimental investigation of the first stage of a two-stage turbine designed for free-vortex flow. The results of the investigation showed that highest adiabatic efficiency was attained when the turbine was operating near the design total-pressure ratio. Results regarding power and efficiency, weight rate of gas flow through the turbine, weight-flow distribution at stator-cascade outlets, stator and rotor flow angles at mean radii, radial distribution of flow angle, radial distribution of the rotor-outlet flow angle, radial distribution of the total pressures at the stator-cascade outlet, and radial distribution of rotor-outlet pressure are provided.

Report presenting an investigation to study the effect of tetraethyl lead, a knock inhibitor, on isooctane. A brief study of ethyl nitrate was also carried out, which demonstrated that it decreased both the delay and critical explosion pressure. Several series of tests were carried out involving different combinations of lead and fuel-air ratio.

Report presenting force testing on an NACA 3-(3)(05)-05 eight-blade dual-rotating propeller at a range of blade angles. Results indicated that good efficiencies can be obtained at high subsonic forward Mach numbers by operation at high blade angle. Results regarding the propeller characteristics, individual power coefficients, effect of forward Mach number on the maximum efficiency of the dual propeller, and effect of small changes in the rear-propeller blade angle on the dual-propeller characteristics are also provided.

Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.

"The use of Stokes' stream function for axially symmetric problems in linearized supersonic flow is discussed. The computation of streamlines away from the body is shown to be facilitated by solving the stream-function problem rather than the potential problem. Use is made of the stream function throughout this report" (p. 1).