A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.

An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.

"The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results" (p. 1).

Report discussing the hydrodynamic characteristics of a flying boat with a low-drag, planing-tail hull compared with a conventional-type hull. The planing-tail model had more take-off stability than the conventional model and had lower hydrodynamic resistance. Information about the landing stability, variation of trim with speed, and spray characteristics is also provided.

Memorandum presenting an analysis to determine, for control design purposes, the approximate response of pressures in the ramjet engine to changes in fuel flow. In the first part, the response after dead time is treated by the linearized lumped-parameter method. In the second, the dead time occurring between the change in fuel flow and the beginning of the pressure response is discussed.

From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."

From Introduction: "The objectives of this report are to present methods and information sufficient for a lineralized dynamic description of the significant dependent and independent variables of a turboprop engine."

"The hydrodynamic characteristics of a flying-boat incorporating a low-drag, planing-tail hull were determined from model tests made in Langley tank number 2 and compared with tests of the same flying boat incorporating a conventional-type hull. The planing-tail model, with which stable take-offs were possible for a large range of elevator positions at all center-of-gravity locations tested, had more take-off stability than the conventional model" (p. 1).

"For about the past year, American Airlines has been engaged in obtaining data on various uses of airborne radar under routine operating conditions. This work is under contract to the Navy Department, Bureau of Ships, and includes the investigation of radar as a navigational aid and terrain collision warning device and its use in icing and turbulence detection. In view of the work of the National Advisory Committee for Aeronautics on atmospheric turbulence, the NACA was requested to participate in the tests to the extent of obtaining and evaluating the turbulence data for use in the turbulence-detection phase of the work" (p. 1).

Memorandum presenting the results of experimental and theoretical data on nine cowls to determine the effect of initial lip angle and projected frontal area on the cowl pressure drag coefficient at Mach numbers from 1.90 to 3.88. Results regarding the surface pressure coefficients, pressure distributions, effect of lip angle, projected cowl area, and Mach number on the cowl pressure drag coefficients are provided.

Report presenting an investigation of an inlet with combined external and internal supersonic compression, formed by spike and cowl oblique shocks, and an overall length of 2.5 inlet diameters at a range of Mach numbers over a range of angles of attack. With proper boundary layer control on the centerbody, this method of internal compression did not adversely affect the high performance of the inlet.

Report presenting testing of a highly polished 9-inch-diameter hemisphere-cylinder in flight in order to obtain boundary-layer transition and heat-transfer data. Results regarding the free-stream conditions, pressure measurements, temperature measurements, heat-transfer measurements, and transition and transition parameters are provided.

The hydrodynamic characteristics of a preliminary design of the Martin XP6M-1 flying boat have been determined. Longitudinal stability during take-off and landing, resistance of the complete model, and behavior during taxiing and landing in rough water are presented.