Report presenting an investigation of boundary-layer bleed through a slot placed at the juncture of the suction surface and end wall to determine whether bleed in this manner could be used to prevent the local accumulation of boundary-layer fluids due to secondary flows. Results regarding the effect of bleed pressure, effect of bleed-slot height, and effect of slot length and position are provided.

"A method is presented for determining the time-dependent flow over a rectangular wing moving with a supersonic forward speed and undergoing small vertical distortions expressible as polynomials involving spanwise and chordwise distances. The solution for the velocity potential is presented in a form analogous to that for steady supersonic flow having the familiar "reflected area" concept discovered by Evvard. Particular attention is paid to indicial-type motions and results are expressed in terms of generalized indicial forces. Numerical results for Mach numbers equal to 1.1 and 1.2 are given for polynomials of the first and fifth degree in the chordwise and spanwise directions, respectively, on a wing having an aspect ratio of 4" (p. 595).

Report presents the results of an investigation conducted to study free-convection heat transfer in a stationary vertical tube closed at the bottom. The walls of the tube were heated, and heated air in the tube was continuously replaced by fresh cool air at the top. The tube was designed to provide a gravitational field with Grashof numbers of a magnitude comparable with those generated by the centrifugal field in rotating-blade coolant passages (10(8) to 10(13)). Local heat-transfer coefficients in the turbulent-flow range and the temperature field within the fluid were obtained.

From Summary: "The results of two investigations, one to determine the relative merits of four experimental and two conventional design 75-millimeter-bore (size 215) cylindrical roller bearings and one to determine the relative merits of nodular iron and bronze as cage materials for this size and type of bearing, are presented in this report. Nine test bearings were operated over a range of dn values (product of bearing bore in mm and shaft speed in r.p.m) from 0.3 x 10(6) to 2.3 x 20(6), radial loads for 7 to 1613 pounds, and oil flows from 2 to 8 pounds per minute with a single-jet circulatory oil feed. Of the six bearings used to evaluate designs, four were experimental types with outer-race-riding cages and inner-race-guided rollers, and two were conventional types, one with outer-race-guided rollers and cage and one with inner-race-guided rollers and cage."

Report presenting an investigation of the rolling-stability derivatives for a model of the Republic F-105 airplane over a range of Mach numbers and angles of attack. The model retained damping in roll through the test ranges, but values of the damping varied considerably with angles of attack. Derivatives of yawing moment and lateral force due to rolling generally followed previously indicated trends.

Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.

Low-temperature chemical starting of combined JP-4 nitric acid propellant for low-thrust rocket engine using three-fluid propellant valve.

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 the results of an investigation to determine the effect of Mach number on the aerodynamic characteristics of a flying-boat hull with a high length-beam ratio. Information about the drag coefficients, angles of attack for minimum drag, and longitudinal and directional stability is 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 a wind-tunnel investigation using the transonic-bump method to determine the longitudinal stability and control characteristics of a semispan airplane model with a 45 degree sweptback wing and tail at transonic speeds. An increase in the rate of change of the pitching-moment coefficient with lift coefficient at a constant Mach number through the transonic range was noted.

From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbers up to 0.94."

Report presenting an analysis of some longitudinal maneuvers obtained during performance tests of the Convair XF-92A by using measured period and time to damp to half amplitude and with a computer to give a preliminary measurement of the airplane stability and damping at a range of Mach numbers. Results indicated that no loss in control effectiveness was shown, the static stability increased with Mach number, the damping was light but positive, and the damping factor was low.

Report presenting a continuation of the program in the high-speed 7- by 10-foot tunnel to investigate the aerodynamic characteristics in pitch, sideslip, and steady roll of model configurations with variations in wing geometric parameters. This report contains the aerodynamic characteristics in pitch of wing-fuselage combinations with wings of aspect ratio 4, sweepback angle of 45 degrees, and three different taper ratios. Results regarding lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratio are provided.

The investigation includes steady and accelerated vertical and longitudinal motions and steady rolling, yawing, sideslipping, and pitching for Mach numbers and aspect ratios greater than those for which the Mach line from the leading edge of the tip section intersects the trailing edge of the opposite tip section. The stability derivatives are derived with respect to principal body axes and then transformed to a system of stability axes. Theoretical results are obtained, by means of the linearized theory, for the surface-velocity-potential functions, surface-pressure distributions, and stability derivatives for various motions at supersonic speeds of thin flat rectangular wings without dihedral.

Memorandum presenting an investigation of flow separation from a flat plate ahead of two blunt two-dimensional bodies in detail at Mach number 2. Interferograms were obtained for the separated regions, and the pitot-pressure distribution and flow directions were surveyed in one of the regions. Results regarding recovery factors and static pressures, density, total pressure, Mach number distribution, and flow-direction survey are provided.

Memorandum presenting flight tests conducted on a thick-lipped nose inlet of a transonic swept-wing aircraft. The total-pressure recovery and distortion at the compressor face were measured over the maneuvering range of the airplane for Mach numbers up to 1.03. Results regarding the radial total-pressure profile, average total-pressure recovery, and total-pressure distortion are provided.

Report presenting an investigation in the Unitary Plan wind tunnel to determine the static stability characteristics of five hypersonic missile configurations. Tests were performed at a range of Mach and Reynolds numbers based on body length. Results regarding the effect of a base block, longitudinal and directional stability, and Reynolds number effect are provided.

Report presenting an investigation to determine the experimental and predicted wave-drag characteristics of wing-body combinations. Two yawed wings, each with an average sweep of about 40 degrees, were tested with various bodies, and the results were compared with existing data for similar models with sweptback wings. Results regarding the aerodynamic characteristics and pressure results are provided.

Report discusses ways to reduce "viscous effects", which increase total pressure losses due to friction at increasing free-stream Mach numbers. Some of the effects are related to the inlet of an aircraft and potential issues in design. From Introduction: "Care must be exercised in inlet design to maintain uniform steady boundary-layer and core flows in the throat."

The effects of inlet circumferential position around the fuselage on the characteristics of a half-conical scoop inlet having a 24.6deg half-angle cone have been investigated in the langley 4- by 4-foot supersonic pressure tunnel. Pressure-recovery results have been obtained at a Mach number of 2.01 for a fixed boundary-layer-bleed height which was 60 percent of the boundary-layer thickness at an angle of attack of 0deg, and for cowling position parameters of 42.4deg and 38.0deg. inlet had a capture area equal to 24.9 percent of the basic-fuselage frontal area. The angle of attack was varied from 0deg to 12deg.

"Aeroelastic instability phenomena of isolated open and closed rigid bodies of revolution free to move under elastic restraint have been investigated experimentally at low speeds by means of models suspended at zero angles of attack and yaw on slender flexible struts from a wind tunnel ceiling. Three types of instability were observed - flutter similar to classical bending-torsion flutter, divergence, and an uncoupled oscillatory instability which consists in nonviolent continuous or intermittent small-amplitude oscillations involving only angular deformations. The speeds at which this oscillatory instability starts were found to be as low as about one-third of the speed at flutter or divergence and to depend on the shape of the body, particularly that of the afterbody, and on the relative location of the elastic axis" (p. 1).

"An investigation was made in the Langley two-dimensional low-turbulence tunnel on a wing section for the XB-36 airplane equipped with a double slotted flap to determine the effect on lift and drag of various slot-entry skirt extension. A skirt extension of 0.787 deg. was found to provide the best combination of high maximum lift with flap deflected and law drag with flap retracted. The data showed that the maximum lift at intermediate (20 deg. to 45 deg.) flap deflections was lowered considerably by the slot-entry extension; but at high flap deflections the effect was small" (p. 1).