Report presenting a method for presenting the preliminary design calculation of high-pressure ratio, multistage, axial-flow compressors using the solid-body inducer-type design. Calculations are presented for various inlet hub-tip ratios, weight flows, and average pressure ratios per stage.

Report presenting an experimental investigation to study the variation of average induced flow around a model helicopter during transition from a hovering condition to steady autorotative vertical descent. Test data were obtained from simulated power failures under many different conditions. Results for variations in disk loading, blade angles, and rate of pitch change are provided.

Note presenting two methods for calculating actual buckling stress, including the author's exact theory and the method of split rigidities, both of which lead almost identical results. Columns with box-, I-, H-, and T-sections and angles are considered separately.

Note presenting an investigation carried out to study the elastic behavior after buckling of a rectangular plate reinforced with longitudinal stiffeners and subjected to compressive loads in a direction parallel to the stiffeners. Two possible buckling modes were investigated.

Report presenting an evaluation of the theoretical performance of the turbine-propeller engine with augmentation by means of compressor-inlet water injection, tail-pipe burning, and a combination of the two methods. An investigation of the effect of augmentation of variations in compressor and turbine efficiency, compressor pressure ratio, turbine-inlet temperature, and propeller-plus-gear efficiency was conducted. The investigation also include the effects of ambient humidity and temperature and degree of evaporation during compression.

"A method of solution is presented for compressible fluid flow past an elliptical cylinder by means of the variational method. The solution is obtained as a function of thickness ratio and free-stream Mach number. Numerical examples are carried out for several thickness ratios and Mach numbers and the results are compared with those obtained by other methods" (p. 1).

Note presenting a wind-tunnel investigation to determine the high-speed subsonic aerodynamic characteristics of NACA 63-, 64-, 65-, and 66-series airfoil sections with four thickness ratios and an ideal lift coefficient with the uniform-load type of mean camber line. For each thickness ratio, only a slightly impairment of high-speed section drag characteristics results from forward movement of position of minimum base-profile pressure up to 40 percent of the chord.

Note presenting an evaluation of the theoretical performance with inlet water injection of an axial-flow compressor operating as a component of a gas-turbine engine for normal compressor pressure ratios of 4, 8, and 16. Continuous saturation throughout the compression process is assumed. Results regarding the compressor-inlet gas flow, compressor performance, and applicability of the analysis are provided.

Note presenting an investigation of the laminar-boundary-layer development over a semi-infinite flat plate placed in a flow with concentric circular streamlines with the limitation of small total turning of the mainstream flow. Results indicated that the profile of the velocity component in the direction of the flow outside the boundary layer is identical to that existing in two-dimensional flow over a flat plate.

Note presenting a radioautographic method that may be used as a convenient method for examining the distribution of particles in a cyclotron beam. The experiments in this report establish the feasibility of the photographic method by showing that the photographic density produced by an active sample is proportional to the beta-ray activity of the sample.

"A method is described for the solution of the nonlinear equations for supersonic conical flow. The procedure is mostly a numerical one based on the method of characteristics and the relaxation process. A procedure for calculating the position of the shock is inherent in the analysis. The method is applicable to any conical flow" (p. 1).

Report presenting equations and charts for computing the thrust, power output, fuel consumption, and other performance parameters of a turbine-propeller engine for any given set of operating conditions and component efficiencies. The total thrust horsepower per unit mass rate of air flow and specific fuel consumption for a wide range of flight and engine-design operating conditions are also presented.

Report presenting a method of analysis for two-dimensional flow on general surfaces of revolution in turbomachines with arbitrary blade shapes. The method of analysis is developed for steady, compressible, nonviscous, irrotational flow that is assumed uniform normal to the surfaces of revolution.

Report presenting a number of the most promising integral methods for solving approximately the compressible-laminar-boundary-layer equations in order to determine a computationally convenient and sufficiently accurate method of calculating boundary-layer characteristics. Approximate solutions can be obtained by assuming special forms for the velocity profiles satisfying various boundary conditions and containing, in practice, either one or two parameters to be determined by the equations.

Note presenting measurements of the local temperature-recovery factor of a turbulent boundary layer produced by natural transition on a thin-walled, metal, 10 degree cone measured at a range of Mach and Reynolds numbers. The recovery factor in the fully developed turbulent zone was found to have a value of 0.0882 which was essentially independent of both Mach number and Reynolds number. Results regarding the 10 degree cone and 40 degree cone cylinder are provided.

Report presenting an investigation of steady flow about curved airfoils at high supersonic speeds. Testing demonstrated that within the limitation of the assumption of ideal gas flow, the shock-expansion method may be used with good accuracy to predict pressure distributions on curved airfoils at arbitrarily high Mach numbers.

Note presenting a revision of the semiempirical method of dealing with shields by treating them as composed of layers by taking the angular distribution of the radiation into account and by making use of the transport equation. The method is illustrated by consideration of the effect upon neutrons of a thick nonabsorbing shield of high atomic weight.

The effects of wing lift and weight on maximum landing gear loads were investigated by drop testing a small landing gear with oleo shock strut in the Langley impact basin. Lift forces were mechanically applied to the dropping mass to produce wing lift factors between 1000 and 2500 pounds. The results show the relationship between lift force, weight, and landing-gear loads for a range of vertical velocities between 0 and 12 feet per second.

Memorandum presenting an investigation of boundary-layer suction and its favorable effect in deferring transition points as long as possible in order to avoid turbulence.

Report presenting free jet tests of a model of the inlets and forebody of the McDonnell XF3H-1 airplane with the original and two alternate nose shapes. Results regarding the total-pressure recovery after diffusion, maximum mass-flow ratio, inlet total-pressure profile, shadowgraphs, flow variation, and pressure oscillations are provided.

Memorandum presenting stability charts covering a range of small positive and negative static margins for a supersonic missile with an autopilot sensitive to angle of pitch and rate of pitch. The results in the form of stability boundaries and lines of constant damping ratio and period show that time lags have an adverse effect on stability, but this can be counteracted by using ample gain in the rate-of-pitch feedback loop. Methods of simplifying the characteristic stability equation are discussed.

Report presenting large-scale tests of a semispan model of a 60 degree sweptback wing-fuselage combination. The model was equipped with 25-percent-chord, 36-percent-span, double-slotted flaps, 25-percent-chord, 43-percent-span ailerons, and 17.5-percent-chord leading-edge slats. Flow separation limited the linear range of the pitching moment of the base wing to a lift coefficient of about 0.35.

Experiments were performed with an apparatus suitable for determining corrosive effects of hot flowing liquids on various container materials. The investigation was conducted with molten sodium hydroxide flowing at a velocity of 15 feet per second. Extensive corrosion and mass trans Extensive corrosion and mass transfer to regions of reduced temperature was observed.

Report presenting estimates of downwash angles determined from an analysis of pressures measured on the horizontal tail of a supersonic aircraft configuration. The results are compared to an approximate application of linearized theory and force-test results for the same configuration.