"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 experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The section was designed to have favorable pressure gradients between the suction slots. The laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the model surface condition as has been found in other investigations.

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 an investigation in the transonic blowdown tunnel at a range of Mach numbers to determine the increments in lift, drag, and pitching moments due to the installation of a semielliptical-shaped air inlet in the root of a 45 degree sweptback wing and to study the internal flow characteristics of the inlet. Results regarding the internal pressure measurements, effect of inlet installation on external aerodynamic characteristics, effect of boundary-layer removal on internal pressure recovery, and inlet performance are provided.

Report presenting testing of supersonic compressor blades with rounded leading edges with an 8-percent mean thickness-chord ratio and a solidity of about 2.5 were incorporated in a 16-inch-diameter rotor with and without guide vanes. Results regarding the overall performance, rotor-blade-element performance, and rotor without guide vanes are provided.

Report presenting an investigation of the lift, drag, pitching-moment, and downwash characteristics of a triangular wing of aspect ratio 3 with an NACA 63A006 section. Downwash was measured by using an all-movable horizontal tail at five locations. Results regarding basic wing characteristics and stability contribution of the tail are also provided.

Memorandum presenting an eight-stage high-pressure-ratio axial-flow compressor designed for use as a research unit in which the problems associated with design and off-design performance of transonic stages combined with highly loaded subsonic stages could be studied. The report discusses the design procedure and presents the experimentally determined overall performance of the compressor.

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 an investigation in the low-turbulence pressure tunnel to determine the lift, drag, and pitching-moment characteristics of two unswept wings, one with airfoil sections designed for high maximum lift at low speeds (NACA 2-006) and one with NACA 65A006 airfoil sections. Results regarding lift and pitching-moment, effects of roughness, drag, and wings with flaps are provided for high- and low-speed performance.

Report presenting an investigation made to improve compressor performance by bleedoff of detrimental boundary layer through a porous compressor casing. The results were compared to the performance characteristics of the original engine. Bleedoff was found to increase the efficiency of the compression process, but the overall performance of the turbojet suffered.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effectiveness of a spoiler-slot-deflector combination in producing rolling moments in the transonic speed range at angles of attack as high as 24 degrees over a range of Mach numbers. The wing had an aspect ratio of 4, a taper ratio of 0.6, an unswept quarter-chord line, and NACA 65A006 airfoil sections.

Report presenting an investigation of the total-pressure-recovery characteristics over a wide range of angles of attack of an axially symmetric nose inlet at a Mach number of 1.42 and an asymmetric nose inlet at Mach numbers of 1.42 and 1.84.

Report presenting a wind-tunnel investigation to study the effects of operating propellers on the low-speed longitudinal characteristics of a four-engine tractor airplane configuration. The coefficients of lift, longitudinal force, pitching moment, propeller thrust, and propeller power are provided. Tests were conducted at a range of Mach and Reynolds numbers.

Report presenting an investigation to develop screech instrumentation and study the mechanism of screech in a simulated afterburner. Results regarding the screech mechanism, effect of system variables on screech, speculation regarding screech mechanism, and suggested techniques for elimination or control of screech are provided.

Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the static stability and control characteristics of a canard-type missile configuration with large deflections of the canard controls and with deflection of wing-tip controls. The results of the investigation indicated that with a 30 degree deflection of the canard control a maximum trim normal-force coefficient of 0.4 and a maximum trim angle of attack of 12 degrees might be obtained for the optimum center-of-gravity location.

Report presenting an investigation of the overall performance of a 20-inch-tip-diameter, eight-stage axial-flow compressor conducted as the initial step in an investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The investigation was made over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed. Results regarding the overall performance, stage performance, comparison with design, and engine application are provided.

From Introduction: "For the analysis reported herein, the same hypothetical 12-stage compressor discussed in reference 6 was chosen, and the effects of inlet-stage stall characteristics and stage interactions were estimated by arbitrary adjustment of the stall characteristics and stage interactions were estimated by arbitrary adjustment of the stalled characteristics of the individual stages."

Memorandum presenting an inlet-type axial-flow compressor rotor with a hub-tip diameter ratio of 0.4 at the rotor leading edge, which was designed, fabricated, and experimentally investigated. The results of the investigation indicated that stages with inlet hub-tip ratios as low as 0.4 can be designed within known practical aerodynamic specifications to produce satisfactory values of stage pressure ratio and efficiency at high specific weight flows.

Report presenting an investigation to determine the performance of a conical-nose supersonic diffuser at angle of attack. The inlet had a pivoting cone which could be oriented to any of several angles independent of the angle of attack of the diffuser. Results regarding total-pressure recovery and mass-flow characteristics, cowl lip position, cone position relative to angle of attack, shadowgraphs, and contour maps are provided.

Report presenting a study of seven additives in 0.5-volume-percent concentration for their effects on the low-pressure limits of flame propagation of propane-air mixtures. Limits were measured in a flame tube of new design. Results regarding propane-air mixtures, propane-air-additive mixtures, and flame propagation qualities are provided.

Report presenting a flight investigation to study in detail the response of an airplane structure during buffeting. Measurements of acceleration on selected points were made during buffeting for two different conditions of lift coefficient and Mach number and the time histories of acceleration were studied using electrical frequency-analysis techniques. Results regarding the ground response measurements, response to buffeting excitation, verification of the measured results, and the pilot's observation of the buffeting 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 visual-flow studies made of the behavior of the vortices which form in the separated flow region in the lee of an inclined body of revolution. Generally, the configuration of vortices in the wake could be changed by varying the position of the crossflow separation lines along the sides of the body. Results regarding the effects of body expansion, effect of body cross-sectional asymmetry, Reynolds number effects, and effects of vortex configuration on body forces are provided.

Report presenting a method to estimate the incompressible-flow surface pressures of compressor airfoils in cascade at design angle of attack by modifying the known pressure distribution as an isolated airfoil. The interference between airfoils was found to vary in a systematic manner. Testing performed on NACA 65-series compressor blade sections appears to agree with estimated values.