Report that is part of a program to investigate the aerodynamic characteristics in pitch, yaw, and steady roll of various model configurations with variations in the wing geometric parameters. The paper presents the aerodynamic characteristics in pitch of wing-fuselage combinations with wings of aspect ratio 4, taper ratio of 0.6, and sweep angles varying from 3.6 degrees to 60 degrees. Results regarding lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratios 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 an investigation in the high-speed wind tunnel to determine the aerodynamic characteristics of three triangular wings and a trapezoidal wing through the transonic speed range by use of the bump technique. Data was obtained over a range of Mach and Reynolds numbers. Results regarding the lift, drag, pitching moment, and lift-drag ratio of the various wings are provided.

Report presenting surveys of the distribution of total pressure, total temperature, and static pressure at a number of stations in the slotted test section and diffuser of the transonic tunnel with early and improved diffuser-entrance noses installed at the ends of the slots. Results regarding power losses with the original diffuser-entrance nose, development of revised diffuser-entrance noses, and energy losses in the tunnel with the final diffuser-entrance nose are provided.

Discusses various insect pests of the Irish potato and how to recognize them. Provides instructions for preparing and applying insecticides.

From Introduction: "In the present paper, which supplements reference 1, V-g records obtained from F8F-2 airplanes in 1949 are analyzed statistically to determine the frequency of experiencing large values of normal load factor and airspeed. These results are compared with the results from the F8F-1 airplane."

Memorandum presenting an investigation conducted to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a cambered and twisted wing with an aspect ratio of 3.0 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for specified Mach and Reynolds numbers. In order to determine the effects of camber and twist, the force, moment, and pressure data are compared with the data for an uncambered and untwisted wing of the same plan form.

Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.

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.

"A brief study was made of the effects of slots in a test-section wall on the reflection from the wall of an incident oblique shock wave at a free-stream Mach number of 1.62. The reflection was observed with an interferometer for various combinations of slot width, spacing, and contour. The reflections from the open and the closed portions of the wall, being at different angles to the wall, were not superimposed and, therefore, did not cancel each other" (p. 1).

"The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking" (p. 1).

Report presenting an investigation to determine the effects of dual-rotation propeller operation at high thrust on the static longitudinal stability characteristics of a semispan powered model representing a twin-engine airplane configuration with flaps retracted. Stability and trim changes associated with an extreme constant power conditions were greatly dependent on tail height and vertical location of the center of gravity. Results regarding basic data, effects of power on overall stability and trim, and tuft-grid flow surveys are provided.

Report presenting free-flight tests made with four fin-stabilized bodies of fineness ratio 8.91 to determine the effect of body cross-sectional shape on body drag at a range of Mach and Reynolds numbers. Results regarding the curve of drag coefficients, drag on the nose and body, and body pressure drag are provided.

Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.

Report presenting an experimental investigation of the flow field downstream of a canard-type control surface and in the vicinity of a symmetrical body in the 8- by 6-foot supersonic tunnel at Mach numbers of 1.8 and 2.0. The results indicated severe total pressure losses and large flow deflections in the control surface wake.

Report presenting general procedures for computing internal pressures in fuel tubes of nuclear reactors and the effects on the pressure of varying neutron flux, fissioning material, and operating temperature.

Report discussing an investigation using rocket-propelled vehicles in free flight to determine the effect of fuselage-diameter - wing-span ratio on the damping-in-roll characteristics of delta wings at a range of Mach numbers. The damping-in-roll derivative was found to decrease when the fuselage-diameter - wing-span ratio was increased. The experimental results are compared to calculated values.

Report presenting an investigation in the full-scale tunnel to determine the effects of symmetrically located wing nacelles on the low-speed aerodynamic characteristics of a 60 degree sweptback delta-wing-fuselage combination. The testing occurred with three spanwise nacelle locations with three chordwise positions at each spanwise station.

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.

From Summary: "Force characteristics determined from tank tests of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions."

Report presenting an investigation to determine the overall performance of the three-stage turbine from the J71 turbojet engine. The turbine operated with a maximum brake internal efficiency of approximately 0.84 at an equivalent overall pressure ratio of approximately 3.6 and an equivalent rotor speed of about 110 percent of the equivalent design value.

Report presenting a program to determine limiting values of the aerodynamic parameters used in turbine design, which includes a study of several turbine designs suitable for application in current aircraft power plants. In this first report, the performance of a single-stage turbine of conservative design was studied for the purpose of establishing a basis for the comparison of turbine performance of less conservative designs.

Report presenting an investigation to determine the effects of camber on the aerodynamic characteristics of a series of rectangular wings with various aspect ratios and thickness-to-chord ratios using the transonic-bump method. Testing occurred over a range of Mach and Reynolds numbers. Lift, drag, and pitching-moment characteristics are presented for wings of 5 aspect ratios, NACA 63A2XX and 63A4XX sections, and 5 thickness-to-chord ratios.

"An investigation of the use of solid fences installed on the side walls of a supersonic wind tunnel to retard the development of transverse flow and thus to increase the uniformity of the side-wall boundary layer is reported. Beneficial results were obtained with fences which had depths of the order of the boundary-layer displacement thickness and which followed potential-flow streamlines through the nozzle. Reduction of the number of fences on each side wall from four to two eliminated their effectiveness" (p. 1).