Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.

Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.

Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.

Report discussing testing on a model of the General Electric P-1 nuclear powerplant to determine its internal aerodynamic characteristics. The main purposes of testing were to measure the mass-flow distribution of air, to measure the total-pressure losses for the duct components and complete model, and to determine modifications necessary to attain the desired performance characteristics.

Report presenting an investigation of ram-jet-engine control by shock positioning on a 16-inch fixed-geometry ram jet at a range of free-stream Mach numbers. The control method appears to offer adequate control of ram-jet-engine operation. Results regarding the steady-state performance, effect of control settings on response and stability, effect of disturbance size and Mach number on response to fuel-flow disturbances, Mach number disturbances, angle-of-attack disturbances, exhaust-area disturbances, and recovery from subcritical engine operation are provided.

Report presenting an investigation to determine the pressure drag of various blunt-based conical afterbodies at a range of Mach numbers. A generalized series of bodies was included which incorporated convergent nozzles discharging unheated jets at various pressures from the base. Results regarding the afterbodies without the jet and afterbodies with the jet are provided.

Report presenting the effects of a straightening operation on the life of Inconel 500 buckets in a J33-9 engine. Results regarding engine performance and bucket-failure mechanism are provided.

Report presenting the typical effects of flow distortions on turbojet-engine performance and how flow distortions can be reduced by reducing the distortion entering the inlet diffuser and by improving the amount of mixing that generally occurs in the subsonic diffuser. Sources of distortion in the supersonic inlet are described and steps are suggested that might be taken to reduce their effects.

Memorandum presenting an investigation in the free-flight tunnel to determine the effect of the sloshing of fuel in partly filled, unbaffled tanks on the lateral stability of a free-flying model. Flight tests were made to determine the effects of the water sloshing for different depths of water and various masses and moments of inertia of the model. The sloshing caused small-amplitude, high-frequency lateral oscillations which were superimposed on the normal Dutch roll oscillation so that the lateral motions of the model appeared jerky.

Report presenting a wing-tunnel investigation in straight and pitching flow to determine the effects of independently varying aspect ratio and angle of sweep on the longitudinal rotary stability characteristics of a series of ten untapered wings. The investigation showed that an interdependent relationship existed between the effects of aspect ratio and sweep. Results regarding pitching moment due to pitching velocity and lift due to pitching velocity are provided.

An investigation conducted in the icing research tunnel on a ramp type recessed fuel cell vent assembly to determine its aerodynamic, rain, and icing characteristics. Although the vent-tube openings are located in the region of maximum ramp pressure, vent-tube static pressures are marginal for a low flight speed.

Report presenting the results of pressure-distribution measurements obtained in flight over the free-blown canopy of a fighter-type airplane. The measurements were compared to those of the same canopy in wind-tunnel testing to determine the degree of correlation and effects of Mach number and distortion on the pressure distribution.

Report presenting the specific impulse, characteristic velocity, thrust coefficient, and heat rejection of liquid fluorine and a fuel consisting of a hydrazine-ammonia mixture for a range of fuel percentages in a 100-pound-thrust rocket engine designed for a combustion-chamber pressure of 300 pounds per square inch absolute. The fuel consisted of 59 percent hydrazine, 37 percent ammonia, and 4 percent water. The attainment of maximum performance with liquid fluorine as a rocket oxidant will require a critical study of injector design.

Report presenting an investigation of the effect of fuselage-mounted rocket boosters on a strut-mounted engine in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.8 and 2.0. The boosters were pairs of circular cylinders with conical forebodies mounted on the top and bottom of the fuselage, and the engine was mounted on a horizontal strut. Results regarding the characteristics of the flow field, effect of putting the boosters in several positions, and effect of angle of attack are provided.

Report presenting an investigation for stationary turbine blades with 10 tubes and 13 fins forming the internal heat-transfer surfaces in order to accurately predict local turbine blade temperatures. Results regarding the comparison of calculated and measured midchord blade temperatures, comparison of calculated and measured temperatures near blade trailing edge, comparison of calculated and measured temperatures near the blade leading edge, the influence of errors in calculated temperatures on design considerations, and an application of the analysis to other blade configurations are provided.

Report presenting measurements in free fall at transonic speeds of the dynamic stability characteristics of three models. Two of the models had 45 degree swept wings of aspect ratio 6 and 45 degree swept tail surfaces and differed only in that one had plane wings and one was cambered and twisted. The third had the same fuselage-tail arrangement but no wing.

Report presenting the results of pressure-distribution and force tests on four wings at Mach number 6.86 and Reynolds number 980,000 in the 11-inch hypersonic tunnel. Characteristics of the wings tested included a 4-inch square plan form, a 5-percent maximum thickness, and diamond, half-diamond, wedge, and half-circular-arc sections. Information about pressure measurements, wing characteristics, and Schlieren photographs is provided.

From Introduction: "An investigation was conducted in an NACA Lewis altitude chamber to determine the altitude performance characteristics of a J47-25 axial-flow turbojet engine over a range of engine-inlet Reynolds number indices corresponding to altitudes from 18,000 to 54,000 feet and flight Mach numbers from 0.50 to 1.10. Reynolds number at a given corrected engine speed and is a function only of engine-inlet total pressure and temperature, was used instead of various set altitudes and flight Mach number combinations (reference 1). An example is included in the appendix to illustrate the method of obtaining conventional performance parameters for a given flight condition from the data such as presented herein."

Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are provided.

Report presenting the performance characteristics of one convergent and three convergent-divergent nozzles obtained over a range of nozzle pressure ratios. Results regarding one-dimensional flow theory and the performance characteristics themselves are provided.

Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.

Report of an investigation of the overall performance characteristics of a complete missile configuration in the 8- by 6-foot supersonic wind tunnel at several Mach numbers, angles of attack, canard-control-surface deflections, and a designated Reynolds number based on wing mean aerodynamic chord. The investigation showed that at a Mach number of 2.0, the addition of engines to a no-engine configuration increased drag and moved the aerodynamic center rearward but produced little additional lift. Results regarding force and moment evaluation and engine-internal-flow evaluation are provided.

Memorandum presenting an investigation of the stability of several bodies of revolution having fineness ratios smaller than 1.0 and having rounded fronts and blunt bases. Free-drop tests were made in the vertical 20-foot free-spinning tunnel to determine the behavior of the various bodies in descent.

The performance characteristics of a downward canted normal-shock side (scoop) inlet located downstream of a triangular control surface are presented for free-stream Mach numbers of 1.5 and 1.8 in terms of total pressure recovery and mass flow ratio for various boundary-layer removal systems, angles of attack, control surface deflections and adverse yaw. An engine operating condition for a hypothetical turbojet engine is established, and the match point characteristics of the engine-inlet configuration are summarized. It is shown that the diffuser performance increases with increased boundary-layer removal and decreases because of the presence of the wake from the forward control surface.