Memorandum presenting the effects of wing modification and stability augmentation on the computed longitudinal behavior in the pitch-up region and probable pilot opinion of the pitch-up characteristics of two current fighter airplanes. An exploration of the addition of a wing-leading edge is included. Results regarding computed pitch-up behavior and probable pilot opinion are provided.

Report presenting the wing-section pressure-distribution and wing-panel load characteristics of the Douglas D-558-II airplane for a range of Mach numbers and airplane normal-force coefficients. At subsonic speeds, the pressure distributions are characterized by a high negative-pressure peak with an abrupt pressure recovery as a result of the leading-edge expansion over the upper surface at moderate angles of attack.

Memorandum presenting a free-flight investigation conducted on four supersonic nose inlets. Each inlet used conical-shock and isentropic-compression center bodies; two of the models had internal contraction and two did not. Results regarding drag coefficient, pressure recovery, mass-flow ratio, and Reynolds number range are provided.

Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.

Report presenting an analysis of losses occurring in a series of subsonic turbine blades in a low-speed two-dimensional cascade and in a related series of four transonic rotors. Results regarding the two-dimensional cascade loss correlations, transonic turbine loss correlations, effect of unsteady flows, and mixing of stator wakes are provided.

Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel at several free-stream Mach numbers for a range of primary-nozzle pressure ratios and secondary weight-flow ratios to determine the effects on performance of varying the ejector diameter ratio by simulated iris flaps. Results indicated that increases in ejector gross force and secondary-to-primary total-pressure ratio were obtained subsonically when diameter ratio was reduced, thus reducing overexpansion losses.

Report presenting an investigation to determine the effect of outer-shell design variables on the internal performance characteristics of plug-type nozzles designed for a pressure ratio between 6 and 12. Inlet Mach number and outer-shell angle were found to have no effect on nozzle thrust coefficient. For choked flow, the effective throat area decreased when the inlet Mach number or outer-shell angle was increased.

Report presenting an investigation of the boattail pressures and base pressures of two twin-jet afterbody configurations at Mach number 1.91. They were designed as a simple merging of two blunt-based conical afterbodies with spacings of 1.4 and 1.7 jet diameters between the jet center lines. Results regarding support-strut interference, effect of jet spacing ratio, effect of jet exit angle, longitudinal boattail pressure distribution, circumferential pressure distributions, and effect of a reflection plane are provided.

Report presenting a review of NACA research on slurry fuels through 1954. Slurry fuels are defined as suspensions of metals in hydrocarbons, which may offer more flight range or thrust than can be obtained with conventional hydrocarbons. Magnesium is the primary metal of interest at this time for high thrust and boron for long-range flight.

The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.

The performance of a 16-stage axial-flow compressor, in which the mean-radius solidity was reduced from 1.28 to 1.02 in the fourteenth through sixteenth stage rotors was determined. The performance of this modification was compared with that of the compressor with original rotors. The reduced solidity resulted in slightly improved performance.

Report presenting an investigation at transonic speeds to determine the maximum lift characteristics of a wing model of the X-1 airplane. Lift, drag, and pitching-moment data for a lift range and range of Mach numbers was collected. Maximum lift was found to be obtained at progressively higher angles of attack as the Mach number was increased.

Report presenting static lateral- and longitudinal-stability tests of a scale model of a projected, low-aspect-ratio, supersonic airplane at low and high subsonic Mach numbers. The wing was equipped with leading-edge flaps and had a modified double-wedge airfoil with sharp leading and trailing edges. Results regarding lift characteristics, static longitudinal stability and control, lateral and directional stability, drag characteristics, and wing and fuselage tuft studies are provided.

From Introduction: "This paper presents the results of the investigation of wing-alone and wing-fuselage combinations employing a wing with the quarter-chord line swept back 35^o, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section."

Report presenting testing on parabolic bodies of revolution of two fineness ratios in the transonic and supersonic range. One had a body fineness ratio of 7.87 and one had a ratio of 12 and were tested under different Mach number ranges. Experimental results and drag estimates of various portions of the body are provided.

Report presenting an investigation of a one-eighth segment of an annular combustor suitable for use as a component of an experimental turbojet engine. Due to the small space available for the combustor, a special design involving a minimum of obstructions in the combustion chamber was created. Results regarding the temperature-rise efficiency, total-pressure loss, and exhaust-gas temperature variation for several simulated engine operating conditions are provided.