Report presenting the average heat-transfer coefficients and equilibrium temperatures for the front half of an isothermal cylinder with a laminar boundary layer as determined by wind tunnel testing at Mach number 6.9 and a range of Reynolds numbers and sweep angles.

Report presenting a transonic compressor rotor with double-circular-arc blade sections, which were designed and tested to investigate the aerodynamic effects of using a short blade chord and a high aspect ratio. The report presents the blade-element performance and performance analysis.

Report presenting static-pressure changes resulting from steady combustion of aluminum borohydride in a supersonic wind tunnel. Static pressures were measured along the top wall of a tunnel adjacent to the flame that filled the upper portion of the test section. Results regarding the static-pressure increases, effect of change in fuel-injection rate, and effect of tunnel boundary layer on the character of the heat-addition region are provided.

Memorandum presenting an investigation made to determine the low-subsonic-speed static longitudinal stability characteristics of a composite-plan-form wing tested as a wing-fuselage combination and as a complete model. Also included is a comparison of the transonic-speed characteristics of the composite-plan-form wing alone and the 45 degree sweptback wing from which the composite wing was derived.

Report presenting an investigation to determine the performance of a Bumblebee 18-inch ram jet with a rake-type flame holder was conducted using kerosene and propylene oxide as fuels. Experiments occurred at a range of pressure altitudes and ram-pressure ratios over the operable range of fuel-air ratios. Use of propylene oxide was found to improve the stability of combustion, increased the operable range of fuel-air ratios, and allowed ignition at high values of combustion-chamber-inlet velocities.

Report presenting an investigation of large-chord flap-type controls with sweptback hinge lines and with various sizes and shapes of horn balances on a triangular wing of aspect ratio 2. Changes in the following elements were investigated: shielding of the horn balance, percentage of horn balance, trailing-edge thickness, flap nose seal, contour of the horn balance, and Reynolds number.

Report presenting an investigation of the stage work distribution and losses through the turbine at design conditions of the XJ35-A-23 two-stage turbine. The investigation showed that the poor performance was primarily due to large whirl velocities at the turbine exit, choking in the second-stage rotor, and a choking condition upstream of the physical blade throat. If these conditions are eliminated, satisfactory two-stage turbine performance can be obtained.

Memorandum presenting a review of the acceleration characteristics of an axial-flow turbojet engine with a fixed-area exhaust nozzle as obtained from transients induced by large steps in fuel flow under sea-level static conditions. Maximum acceleration and thrust appeared obtainable through the use of a proposed fuel schedule that required only small initial steps in fuel flow. Results regarding linearity, maximum acceleration and thrust, and fuel-flow schedule are provided.

Report presenting testing of two ceramals for use as gas-turbine blade materials. Results regarding the tensile strength, modulus of rupture, thermal shock, and turbine-blade evaluation are provided.

Report presenting a low-speed investigation of a large-scale model with a 45 degree swept wing of aspect ratio 3.5 and taper ratio 0.3. Wing-fuselage configurations with high-lift devices designed to delay the occurrence of stalled flow to a specific high lift coefficient at a specific angle of attack were tested. Results regarding the lift and drag characteristics, pitching-moment characteristics and effective downwash, rolling-moment characteristics, and performance characteristics are provided.

Memorandum presenting an investigation in the 9-inch supersonic tunnel to ascertain the lift, drag, and pitching moment associated with typical body-bomb-bay combinations with and without the bomb. Measurements were made at a range of angles of attack, Mach numbers, and Reynolds numbers.

Memorandum presenting measurements of the dielectric constant for suspensions of two types of boron powder in mineral oil as a function of concentration of boron particles, moisture content, temperature, and frequency of oscillation. Also investigated were the effects of boron-powder concentration and moisture content on the dielectric losses of mineral-oil suspensions of the two boron powders.

Memorandum presenting a procedure in the form of charts which permits the rapid estimation of the natural bending frequencies of helicopter rotor blades, both rotating and nonrotating. An evaluation of the method with regard to such things as higher modes, blade offset, and variable mass and stiffness distributions is also given. The valuation shows that, when nonrotating beam bending modes are used, Southwell's equation yields reasonably accurate bending frequencies for rotating helicopter blades.

"An experimental investigation was made by the free-fall recoverable-model technique to assess at zero lift the possibilities of reducing the drag-rise coefficients of a wing-body-cruciform-tail combination by adding volume to the fuselage. The basic features of the test model were an unswept aspect-ratio-3.1 thin wing, a fineness-ratio-12.4 fuselage, and four 45 degrees sweptback tail surfaces. The tests covered a Mach number range of 0.84 to 1.15 with Reynolds numbers of 6.000.000 to 14,000,000, based on the wing mean aerodynamic chord" (p. 1).

From Summary: "An investigation was conducted at simulated high-altitude flight conditions to evaluate the use of compressor evaporative cooling as a means of turbojet-engine thrust augmentation. Comparison of the performance of the engine with water-alcohol injection at the compressor inlet, at the sixth stage of the compressor, and at the sixth and ninth stages was made. From consideration of the thrust increases achieved, the interstage injection of the coolant was considered more desirable preferred over the combined sixth- and ninth-stage injection because of its relative simplicity."

"An investigation has been made at high subsonic speeds of the aerodynamic characteristics in pitch and sideslip of a 1/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for small sideslip angles at Mach numbers above 0.8; however, the instability was eliminated by several different modifications" (p. 1).

Report presenting wing-flow-method measurements for 0.47 to 1.15 Mach number of the longitudinal-stability and -control characteristics of a triangular wing of aspect ratio 2 equipped with a constant-chord flap. Changes in the lift-curve slope and aerodynamic-center position through the transonic speed range were moderate and gradual. Results regarding triangular-wing characteristics, flap characteristics, and a comparison of the wind-tunnel and free-flight-test results at higher Reynolds numbers are provided.

"This paper presents some data on the dynamic lateral stability characteristics of the Douglas D-558-II (BuAero No. 37974) airplane. For the airplane in the clean condition, the lateral oscillations are lightly damped. In the landing condition, the airplane performs a constant-amplitude lateral oscillation" (p. 1).

Report presenting wind-tunnel tests at Mach numbers of 2.0 and 2.9 to investigate the aerodynamic characteristics of several configurations of a supersonic ram-jet test vehicle. Three low-aspect-ratio wing configurations, with the ram-jet engine located forward and below the wing, were tested in pitch at Mach number 2.0.

Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.