"Calculations have been made to determine the effects of Mach number and altitude on the lateral frequency response, the lateral response to a lateral sinusoidal gust distribution, and the period and damping of the lateral oscillation for the North American F-86A, Grumman F9F-2, Republic F-84, Douglas D-558-II, and Bell X-1 airplanes without autopilots. Aeroelastic and unsteady lift effects have not been included in the calculations and may have a large effect on the results for certain flight conditions. The results of the investigation are presented, without analysis, for reference purposes" (p. 1).

Memorandum presenting an investigation made of the effects of store mounting on the buffet, trim, and drag characteristics of fuselage-mounted external stores between Mach numbers of 0.7 and 1.4 by the use of the rocket-propelled-model technique. Results of the tests are presented in the incremental accelerations in the stores due to buffeting, trim normal- and side-force coefficients, tail helix angles, and drag coefficients plotted against Mach number.

Report presenting the flow-generation and shock-wave-reflection characteristics of a two-dimensional tunnel with 24-percent-open, deep, multislotted walls. The deep multislotted wall proved unsatisfactory as a means of reducing boundary-reflected disturbances, because a mixed disturbance was reflected from the wall. Results regarding flow generation, shock-wave reflection, subsonic operation of test section with deep multislotted walls, and outflow requirements are provided.

Report presenting a theoretical investigation to determine the effects of control-surface-servo natural frequency on the transient characteristics of a flight-path-angle control system for three values of airframe static margin and five flight conditions. Results regarding response time, attitude accuracy, total volume of oil flow, peak rate of oil flow, and maximum normal acceleration for the missiles tested are provided.

"An investigation was conducted on a 35 degree swept-wing model to determine the aerodynamic characteristics and suction requirements of a model having a leading-edge area-suction flap deflected 40 degrees" (p. 1). The procedures, corrections needed, force characteristics, suction requirements, and pressure distributions are described.

Report presenting an experimental investigation to determine the porosity characteristics of perforated materials for normal and parallel flow. The results indicated that the porosity of the material is primarily governed by its open ratio, but that density has a slight effect. When the material was tested under parallel-flow conditions, the effective porosity dropped markedly as the stream velocity increased.

Report presenting formulas for fifteen elastic constants associated with bending, stretching, twisting, and shearing of plates with closely spaced integral ribbing in a variety of configurations and proportions. Four coefficients are provided for each rib and the experimental means of determining them are described.

Report presenting a free-flight longitudinal-stability investigation between Mach numbers of 0.85 and 1.34 to obtain the aerodynamic characteristics of a long-range, jet-propelled, ground-to-ground missile with a wing of aspect ratio 5.5, 45 degrees of sweepback, and taper ratio 0.4 on a body with a vertical tail. Two models with two different wing materials were flown. Results regarding trimmed flight, pitching flight, and aeroelastic calculations are provided.

"In an attempt to improve the longitudinal stability characteristics of the Bell X-5 research airplane at 59 degrees sweepback, the wing-root leading edge was modified by replacing the original 52.5 degrees sweptback leading-edge fillets with rounded leading-edge fillets. The data obtained show that the longitudinal stability characteristics, as well as the buffet and drag characteristics, were unaffected by the modification" (p. 1).

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.

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.

Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.

Report presenting an investigation of systematic series of sharp- and blunt-trailing-edge wings to determine the effects of thickening the trailing edges on the lift, drag, and pitching moment characteristics at several Mach numbers. Results indicate that no appreciable zero-lift drag reduction can be obtained by thickening the trailing edges from 1.41 to 1.96, but trailing edges can be thickened appreciably with no increases in zero-lift drag.

Report presenting a wing-flow investigation to determine the lift, pitching-moment, and hinge-moment characteristics of an unswept and untapered NACA 65-009 airfoil model with an aspect ratio of 3.01 and a 1/4-chord full-span plain flap. Effects of sealing a portion of the length of the flap gap were investigated as well as adding roughness to a portion of the airfoil chord. Information about the maximum unstalled lift coefficient, compressibility phenomenon, and hinge-moment coefficient is also provided.

A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Data are being obtained on characteristics in pitch, sideslip, and during steady roll at Mach numbers from 0.40 to about 0.95. This paper presents results which show the effect of taper ratio on the aerodynamic characteristics in sideslip of wing-fuselage combinations having wings with a sweep of 45 degrees at the quarter-chord line, an aspect ratio of 4, and a NACA 65A006 airfoil section.

From Summary: "An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area."

"A mixed-flow impeller was designed to give a prescribed blade-surface velocity distribution at mean blade height for a given hub-shroud profile. The blade shape at mean blade height, which was produced by the prescribed velocity distribution, was extended by means of radial lines to form the composite blade shape from hub to shroud. The resulting blade was relatively thick; therefore, it was necessary to retain the inverse blade taper which resulted from extension of the radial lines in order to prevent merging or near merging of the separate blades near the hub. For the first test version of the impeller, designated the MFI-2A, the blade height was arbitrarily made greater than that for the basic impeller (the MFI-2) to allow for viscous effects" (p. 1).

A turbine designed to power a supersonic compressor was investigated with four nozzle settings and one nozzle modification to determine the effect on turbine performance. With the correct ratio of nozzle throat area to rotor effective throat area, the design specific work was obtained near the peak efficiency. From the results of the investigation it was concluded that the convex in sweep of the rotor inner wall and high degree of blade taper caused the turbine configuration to have two aerodynamic disadvantages in comparison with a turbine configuration with an axial inner wall at the rotor outlet and little axial taper.

"An analytical and experimental investigation was made with a J33-A-9 engine to determine the effectiveness of spray cooling as a means of increasing thrust by permitting engine operation at inlet-gas temperatures and speeds above rated. With the assumption of adequate spray cooling at a coolant-to-gas flow ratio of 3 percent, calculations for the sea-level static condition indicated a thrust may be achieved by engine operation at an inlet-gas temperature of 2000 degrees F and an overspeed of 10 percent. Of the water-injection configurations investigated experimentally, those located in the inner ring of the stator diaphragm provided the best cooling at rated engine speed" (p. 1).

Report presenting some measurements of the dynamic lateral stability and lateral and longitudinal trim of a Douglas D-558-II in flights up to a Mach number of 1.87 and an altitude of about 67,000 feet. Testing indicated that the airplane flying in low density air at supersonic speeds had poor dynamic lateral stability, which worsened as the Mach number was increased to 1.85.

Memorandum presenting an investigation of the effects of longitudinal location of the wing and varying body size on the interference characteristics of a 45 degree sweptback wing over a range of Mach numbers and angles of attack. The wing had an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections. The results indicated that the zero-lift drag of the wing with interference in the forward position was lower throughout the Mach number range than for the wing with interference in the rearward position.

Report presenting an investigation to determine the performance characteristics of a double-shroud cooling-air ejector configuration. Two convergent nozzles were used to simulate a specific manufacturer's iris-type variable-area nozzle in the open and closed positions. The investigation had four phase: (1) obtaining performance with no secondary or tertiary air flow, (2) determining the tendency for backflow to occur in either cooling-air passage, (3) determining the sensitivity of flow in one passage to the other, and (4) obtaining pumping and thrust characteristics with secondary and tertiary air flow.

Report presenting two-group criticality calculations for sodium-hydroxide-cooled, moderated, and reflected reactors for various concentrations and compositions of reactor fuel-element structural material. The investigation was performed in order to determine the applicability of the fuel properties to power a nuclear aircraft. Results regarding the specific reactor calculations, reflector savings, criticality generalization, typical neutron flux and heat-generation distributions, static stability characteristics and excess uranium requirements, reactor heat-transfer characteristics, and airplane and turbojet cycle characteristics are provided.

Report presenting results of two-group criticality calculations for sodium-hydroxide-cooled, moderated, and reflected reactors for various concentrations and compositions of reactor fuel-element structural material. Based on turbojet-engine cycle operating conditions optimized for minimum airplane gross weight, the maximum reactor fuel-element and coolant temperatures are related to the reactor heat release and airplane gross weight for a range of reactor heat-transfer variables.