Report presenting an extension of NACA RM A52C14 about inlet design and performance for Mach numbers of 1.5 to 2.0. A two-dimensional inviscid analysis is used to compare the performance of several types of inlets when used in conjunction with a turbojet engine with constant-volume air flow. Results regarding air delivery and air requirements, drag factors, evaluation of inlet performance, significance of the drag summation, and inlet and engine-matching considerations are provided.

A study of the effects of variations in lateral-oscillatory characteristics on air-to-air tracking performance has been made, using a conventional, propeller-driven fighter airplane equipped with servo devices for varying these characteristics in flight. Tracking runs were made both in smooth air and in simulated rough air. The lateral-oscillation period, damping, and roll coupling were varied over wide ranges during the investigation.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a body-control arrangement at Mach number 1.61. A 70 degree delta canard-type control mounted in the horizontal plane and with a span-to-body-diameter ratio at the control trailing edge of 2.52 tested both fixed and moving in the presence of a long cylindrical body with a parabolic nose.

From Introduction: "The over-all altitude-performance characteristics of this engine are reported herein, and the component performance characteristics are given in reference 1. The data are presented in the form of engine pumping characteristics to allow accurate calculation of engine performance at any operating or flight condition within the range covered by the experimental data. A curve is also presented that will allow determination of thrust in flight by the measurement of ambient static pressure and total pressure in the exhaust nozzle."

Report presenting an investigation in a duct system with fully developed pipe flow to determine the effects of vortex generators on the performance of a diffuser with whirling inlet flow. Testing was made with three different inlet whirl angles and rectangular, noncambered airfoils that varied in chord, span, angle setting, number, and location. Results for the 20.6 degree inlet whirl angle, 15.2 degree inlet whirl angle, 0 degree inlet whirl angle, and effect of inlet whirl angle on diffuser performance are provided.

Report presenting an investigation of the total-pressure-recovery characteristics over a wide range of angles of attack of an axially symmetric nose inlet at a Mach number of 1.42 and an asymmetric nose inlet at Mach numbers of 1.42 and 1.84.

Report presenting an investigation to determine the low-speed chordwise pressure distributions near the midspan station of the slotted flap and aileron of a model of the Bell X-1 airplane with a wing of aspect ratio 4, taper ratio 0.5, 0 degree sweepback of the 40-percent-chord line, and a modified NACA 64A004 airfoil section. Results regarding section pressure distribution and section normal-force and pitching-moment coefficients are provided.

An investigation of a method of preparing intricately shaped objects such as turbo-supercharger blades from refractory powders. The method consists of preparing an extremely thick slip of materials like titanium carbide with a small amount of binder, casting the slip in a mold, and freezing to retain the shape of the casting. Results regarding the applicability of the method and factors affecting soundness, are provided.

Report presenting flight testing of a 60 degree delta wing (NACA 65A003 airfoil section) mounted in midwing and high-wing positions on a modified transonic body from Mach numbers 0.8 to 2.0. The high-wing configuration without nacelles had higher drag coefficients than the midwing configuration without nacelles, but both configurations had approximately the same longitudinal distribution and frontal area. Results regarding nacelle internal drag, configuration drag, nacelle drag coefficient, and normal-force coefficient are provided.

Report presenting an investigation to determine the altitude performance characteristics of a J73-GE-1A turbojet engine conducted in an altitude chamber. The engine had a ten-percent oversize turbine-nozzle are compared with the production J73 engine. Results regarding radial pressure and temperature profiles, compressor performance, combustor performance, turbine performance, and tail-pipe-diffuser and exhaust-nozzle performance.

Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 turbojet engine was determined in the Lewis altitude wind tunnel over a range of altitudes from 5000 to 55,000 feet and flight Mach numbers from 0.28 to 1.05. Data were obtained for each of four exhaust-nozzle areas and are presented in graphical and tabular form.

Report presenting testing of a ram-jet canard missile model with a wing and horizontal and vertical canard surfaces of delta plan form with 70 degree swept leading edges in the supersonic pressure tunnel. Two ram-jet nacelles were mounted in the vertical plane near the rear of the body and various combinations of components were tested. Results regarding the longitudinal and lateral characteristics, comparison with theory, and effect of nacelles on the model are presented.

From Introduction: "A theoretical investigation was conducted in order to determine what effect the differences in aerodynamic characteristics would have on the short-time response to elevator control of this type of airplane as compared with the responses of a conventional airplane, without regard to any possible psychological influences. The results of this investigation are presented in this paper."

Report presenting an investigation to determine the effect of circumstantial inlet location on the performance of twin half-conical scoop-type inlets with and without boundary-layer removal at several Mach numbers and angles of attack. For positive angles of attack, higher pressure recovery performance was obtained with the inlets mounted on lower fuselage quadrants than on upper quadrants.

Memorandum presenting a supplementary investigation conducted in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement upon the spin and spin-recovery characteristics of a 1/20-scale model of the McDonnell F2H-3 airplane. Results regarding the tests with wing-tip tanks installed and with the experimental aerodynamic shape installed are provided.

Report presenting an experimental investigation to determine the performance of seven full-size ejector configurations over a range of secondary to primary air-flow ratios, primary total- to ambient-pressure ratios, and primary gas temperatures. Results regarding primary-nozzle performance, ejector performance, typical ejector characteristics, effect of operating temperatures on ejector flow characteristics, and effect of geometry on ejector performance are provided.

"The static lateral, directional, and longitudinal stability characteristics of a 0.06-scale model of the Martin B-61A missile (Matador) were investigated in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 t o 1.12. Six-component force and moment data were obtained from strain-gage measurements. The characteristics of a spoiler and of wing-tip end plates were also investigated. The Reynolds number of the tests based on the mean aerodynamic chord of the wing was approximately 1.6 X 10(exp 6)" (p. 1).

Report presenting an investigation conducted to determine the importance of the mixing loss downstream of a blade row with respect to blade profile loss for compressible flow conditions. Theoretical and experimental results and the application of mixing loss results to the example transonic turbine are provided.

Memorandum presenting an investigation made to valuate the effects of vertical height of the horizontal tail on the static longitudinal stability of a model with a wing with 35 degrees of sweepback, an aspect ratio of 4.5, a taper ratio of 0.5, and NACA 64A010 sections. The investigation also included the effects of adding a partial-span, leading-edge chord extension to the outer portions of the wing. Results regarding the effect of tail height, wing-wake and local downwash measurements, and effect of a leading-edge extension are provided.

Memorandum presenting an investigation made of the effects of circular end plates on the aerodynamic characteristics of a modified triangular wing of aspect ratio 2 and taper ratio 0.33. The experimental results show that the addition of end plates produces so slight a difference in the total change in static longitudinal stability with Mach number in the range from 0.6 to 1.9 that no beneficial effects on the trim drag may be realized.

Report presenting a wind-tunnel investigation on 3.5-percent-thick symmetrical double-wedge delta wings to determine the effects of thickness distribution on lift, drag, and pitching moment. Six maximum-thickness positions were tested on three basic wings at different Mach numbers and Reynolds numbers. Results regarding lift, drag, the lift-drag ratio, and the center of pressure are provided.

Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.

Report presenting a method using charts for the systematic determination of a corrugation geometry configuration which, for a specific application to an air-cooled turbine blade, gives the required amount of blade temperature reduction using the minimum amount of coolant flow within pressure-drop limitations. A numerical example is included to illustrate the use of the method.

Report presenting a method to estimate the incompressible-flow surface pressures of compressor airfoils in cascade at design angle of attack by modifying the known pressure distribution as an isolated airfoil. The interference between airfoils was found to vary in a systematic manner. Testing performed on NACA 65-series compressor blade sections appears to agree with estimated values.