Report presenting a theoretical analysis of the air flow through the blade coolant passages in an air-cooled turbine rotor. The simultaneous effects of area change, compressibility, wall friction, heat transfer, and rotation were included.

Report presenting the application of an estimation of the derivative of yawing moment due to rolling to the dynamic lateral stability characteristics of the Bell X-2. Results regarding the airplane with flaps and gear retracted and airplane with flaps and gear lowered are provided.

Report presenting an investigation in the 4- by 4-foot supersonic tunnel to determine the static longitudinal stability and control characteristics of a supersonic aircraft configuration at a Mach number of 1.59. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line.

Report presenting testing of two water-cooled turbines, one of aluminum alloy using forced-convection cooling and one of stainless steel using natural-convection cooling, to obtain heat-transfer and general operating data like blade temperatures, coolant-flow rates, and coolant pumping losses. Results regarding outside and inside heat-transfer results, coolant pumping power, general operating results, and practical considerations for both are provided.

Report presenting testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.

Report presenting an investigation of an NACA submerged inlet operating over a range of mass-flow ratios and oncoming flow angles through a range of Mach numbers by use of a transonic bump. Results regarding the ram-recovery ratio, pressure distributions, and tuft studies are provided.

Report presenting an investigation in the full-scale tunnel of the low-speed longitudinal characteristics of a 47.5 degree sweptback wing-fuselage combination with various extensible leading-edge-flap and plain trailing-edge-flap arrangements. Results regarding the basic longitudinal characteristics, extensible leading-edge flaps, plain trailing-edge flaps, and flap combinations are provided.

Note presenting a practical method, employing a lofting technique, for determining the profile coordinates of an air inlet for the leading edge of an airfoil from formulas which are dependent only on the airfoil coordinates and on the height of the opening. It was found that the base-profile concept of thin-airfoil theory could be applied to a ducted airfoil with satisfactory results. Results regarding design inlets, modified inlets, and end-closure shape are provided.

Report presenting results of a tank investigation of a 1/8-size powered dynamic model of the Grumman JRF-5 airplane fitted with tandem hydro-skis and auxiliary wing-tip skids suitable for operation on water, snow, and ice. Results regarding take-off and landing tests are provided.

In determining the experimental performance of an air-cooled turbine, the heat-transfer characteristics must be evaluated. The suggested formulas that are required to determine these characteristics are presented. The formulas have a form in which dependent parameters are expressed as unknown functions of independent parameters. Methods of experimenting to determine these functions are suggested. In some cases general heat-transfer discussions that lead to the suggested forms of the formulas are given.

In the determination of the performance of an air-cooled turbine, the cooling-air-flow characteristics between the root and the tip of the blades must be evaluated. The methods, which must be verified and the unknown functions evaluated, that are expected to permit the determination of pressure, temperature, and velocity through the blade cooling-air passages from specific investigation are presented.

Report presenting measurements of wing and fuselage pressure distributions made at low and high subsonic Mach numbers on a scale model of the projected X-3 research airplane. Tests were conducted in pitch and yaw and included measurements of the total pressure in the fuselage boundary layer at the location of the left boundary-layer bleed scoop.

Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.

Report presenting the vibration characteristics of several symmetrical ball-root-type blades simulating the mass and natural frequency of axial-flow-compressor blades under various mounting conditions by subjecting them to controlled periodic excitation and centrifugal loading. Results regarding loose single ball-root mounting, loose-lubricated, single ball-root mounting, double ball-root mounting, and damping measurements are provided.

"An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel to determine the static lateral stability characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results of the investigation indicated high directional stability that decreased with increasing Mach number and positive effective dihedral that was essentially invariant with lift coefficient and Mach number" (p. 1).

Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.

Report presenting the results from several recent flights on the Northrop X-4 No. 2 airplane, including the longitudinal stability characteristics over a range of Mach numbers in straight and accelerated flight and the short-period longitudinal-oscillation characteristics.

Report presenting an investigation to determine the longitudinal control characteristics of deflectable wing-tip elevators on a low-aspect-ratio, untapered, 45 degree sweptback semispan wing. The elevators had triangular and parallelogrammic plan forms and flat-plate profiles. Results include the elevator effectiveness and comparison of the elevator effectiveness of deflectable wing-tip controls and trailing-edge flap-type controls.

"Calculations have been made to find ranges attainable by bombers of gross weights from l40,000 to 300,000 pounds powered by turbine-propeller power plants. Only conventional configurations were considered and emphasis was placed upon using data for structural and aerodynamic characteristics which are typical of modern military airplanes. An effort was made to limit the various parameters invoked in the airplane configuration to practical values" (p. 1).

Report presenting additional wind-tunnel tests of a model of the X-3 airplane at low and high subsonic numbers to investigate the lateral and longitudinal-stability and control characteristics. Results regarding the aerodynamic characteristics in pitch and aerodynamic characteristics in yaw are provided.

Report presenting force testing on an NACA 3-(3)(05)-05 eight-blade dual-rotating propeller at a range of blade angles. Results indicated that good efficiencies can be obtained at high subsonic forward Mach numbers by operation at high blade angle. Results regarding the propeller characteristics, individual power coefficients, effect of forward Mach number on the maximum efficiency of the dual propeller, and effect of small changes in the rear-propeller blade angle on the dual-propeller characteristics are also provided.

An investigation was conducted to determine the effects of water injection on the over-all performance of a modified J33-A-27 turbojet-engine compressor at the design equivalent speed of 11,800 rpm. The water-air ratio by weight was 0.05. With water injection the peak pressure ratio increased 9.0 per- cent, the maximum efficiency decreased 15 percent (actual numerical difference 0.12), and. the maximum total weight flow increased 9.3 percent.