Force and pressure distribution studies to high angles of attack on all-movable triangular and rectangular wings in combination with body at supersonic speeds. The ranges of aspect ratios were, for the triangular wings, 3/8 to 4, and for the rectangular wings, 1 to 3.

Report presenting an experimental investigation to determine the effects of simulated engine nacelles on the flutter characteristics of a cambered A-plan-form wing with 45 degree sweepback of the leading edge, an aspect ratio of 3.6, and a taper ratio of 0.14. Results regarding a wing-mount fixed and a model with wing mount free are provided.

Report discussing the flutter characteristics of several control-surface configurations, including a wing with tip ailerons, an all-movable stabilizer, vertical tails with trailing-edge rudders, a t-tail, and some simple models of all-movable controls. Some trends of the configurations and suggestions for improving the flutter characteristics are provided.

Report presenting an investigation of the surface pressures of the outer and inner surface of the bubble-type canopy in order to determine their load requirements. Testing was performed on a Grumman F8F-1 airplane. The forces on the canopy was found to be the highest when the airplane is operating at high speed with the canopy closed.

An altitude-chamber investigation of British Rolls-Royce Nene II turbojet engine was conducted over range of altitudes from sea level to 65,000 feet and ram pressure ratios from 1.10 to 3.50, using an 18.00-inch-diameter jet nozzle. The 18.00-inch-diameter jet nozzle gave slightly lower values of net-thrust specific fuel consumption than either the 18.41- or the standard 18.75-inch-diameter jet nozzles at high flight speeds. At low flight speeds, the 18.41-inch-diameter jet nozzle gave the lowest value of net-thrust specific fuel consumption.

Report presenting flight testing of a missile model with cruciform, triangular, interdigitated wings and tails to determine the longitudinal stability and control characteristics over a range of Mach numbers. Results regarding static stability and damping, control effectiveness, and control hinge moments are provided.

Report presenting a theoretical investigation of an automatic control system with primary sensitivity to normal accelerations as used to control a specific supersonic canard missile. The control system is made up of an integrating servomotor that receives a signal from an accelerometer that is sensitive to normal accelerations of the airframe that it is controlling. The acceleration control system appears to work well for obtaining longitudinal control, but works best when combined with a homing seeker or guidance system for controlling directional space.

From Summary: "This paper supplements a previously published one on the effect of design parameters on ditching characteristics. The supplementary information is based on additional data available from both model tests and full-scale experience. In addition, summary tables compiled from the NACA model ditching investigations are presented."

"A complete stage of an axial-flow compressor designed to produce a high pressure ratio was investigated at speeds from 110 to 130 percent of design speed (836 ft/sec). The data obtained and the results of a previous investigation of the same compressor at speeds from 50 to 100 percent of design speed were used to determine the effect of Mach number on over-all performance. The peak total-pressure ratio increased from 1.095 to 1.515 and the peak adiabatic efficiency decreased from 0.93 to 0.89 as the relative inlet Mach number increased from 0.34 to 0.77. At a relative inlet Mach number of 0.91, a total-pressure ratio of 1.635 was obtained at an adiabatic efficiency of 0.74" (p. 1).

Report presenting an aerodynamic investigation in the high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamic characteristics of wings with 35 and 45 degrees of sweepback, aspect ratio 6, and taper ratio 0.60. The wings were tested over a range of Mach numbers.

Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a 47.7 degree sweptback wing-fuselage combination with split flaps and several modifications. The lift characteristics, pitching-moment characteristics, drag characteristics, and a comparison with flaps of the slotted type are included.

The use of inlet guide vanes with the 24-inch supersonic compressor resulted in a decrease in maximum pressure ratio and adiabatic efficiency, and a slight increase in equivalent mass flow. The loss in total pressure and efficiency resulted from reduced diffusion in the rotor-blade passages, increased shock losses at the higher entrance Mach number, and increased mixing separation, and transfer of mass flow toward the rotor hub. The unsteady flow field created at the compressor entrance by the guide-vane wakes is also responsible for some of the losses. This inherent loss will be encountered whenever inlet guide vanes are used with the shock-in-rotor type of supersonic compressor.

Studies of the stalling characteristics show that the stall begins at the tip and moves inboard with increasing angle of attack at positive sweep; the sta11 begins at root and moves outboard at negative sweep (sweepforward). At +/-45 deg sweep the stall was less sharply defined than at the lower angles of sweep. No effect of Mach number on the.flow patterns as indicated by tufts was found in the speed range of these tests which extended to a Mach number of 0.55.

Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.

Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.

From Introduction: "Design studies of long-range supersonic missiles indicate the Mach number range of 3 to 4 to be of considerable promise. Accordingly, the NACA is conducting research on the performance of a wide variety of supersonic diffusers in this range. The initial phase of this research is concerned primarily with the characteristics of conventional axially symmetric diffusers operating at design values of flight Mach number."

Report presenting a study of the literature data on the solubility of water in hydrocarbons, which includes information about the log of solubility, critical solution temperature, and ratios that may affect solubility are provided. An equation is presented and applied to a few petroleum fractions ranging from gasoline to lubricating oil, and a comparison of calculated and experimental solubilities is provided.

Report presenting an investigation to determine if certain combinations of design nozzle-exit velocity distribution and wall contouring can alter the three-dimensional flow characteristics such that nozzle mass flow cannot be predicted by ordinary two-dimensional design techniques. Four nozzle configurations with different wall contours and velocity distributions were tested. Results regarding the comparison of analytical and experimental values of mass flow are provided.

"An investigation was conducted to determine the effect of porous area suction applied to the knees of full-span leading-edge and part-span trailing-edge flaps installed on an unswept-wing airplane model" (p. 1). The results obtained from an angle of attack of 0 degrees and greater than 0 degrees are compared. The effect of deflection, suction requirements, and stability characteristics are described.

Report presenting testing of some of the flutter characteristics of a 1/4-scale model of the X-1E airplane wing and aileron in the transonic tunnel. The wing was tested as part of a complete model of an airplane over a Mach number range of 0.4 to 1.05 and a range of angles of attack. No stall flutter or classical flutter was encountered, but the results indicate that unstable aerodynamic damping is present on the ailerons at transonic speeds. Results regarding free play, angle of attack, aileron viscous dampers, and aileron tabs are provided.

Report presenting an investigation conducted in the 9- by 9-inch Mach number 4 blowdown jet to determine the aerodynamic characteristics of two double-wedge-section delta wings of aspect ratio 1.3 and 2.3 to angles of attack of 50 degrees at a Mach number of 4.07. The results are compared with the predictions of linear theory, two-dimensional shock-expansion theory, Newtonian-impact theory, and a method which utilizes the shock-wave and expansion-wave equations expanded by the two-dimensional hypersonic-flow similarity parameter.

Report presenting a description of an NACA propeller research vehicle, the McDonnell XF-88B airplane, and the results of testing undertaken with it to determine the aerodynamic characteristics of a supersonic propeller at speeds up to a flight Mach number of 1.01. Results regarding thrust distributions, variation of aerodynamic characteristics with Mach number, installation effects, and a comparison of experimental results with theoretical calculations and other data are presented. The propeller efficiency was measured at 78 to 79 percent and thrust distributions were of a uniform nature.

Report presenting an investigation to determine the pressure-recovery and mass-flow characteristics of an inlet configuration designed to be less sensitive to positive angle-of-attack operation than a conventional conical inlet. Results regarding the straight plate, plate swept 47.5, plates swept 42 degrees and 24 degrees, perforated plates, and a general comparison are provided.

Report presenting the static-thrust characteristics of the NACA 8.75-(5)(05)-037 dual-rotation propeller with six and eight blades as obtained on the static test stand in the course of an investigation set up primarily for studying blade vibratory stresses. Force data were obtained for a blade-angle range measured at the 0.75 radial station on the front propeller. Results regarding the effect of tip Mach number, effect of number of blades, and effect of blade angle are provided.