From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."

Report presenting the results of an investigation of the internal dynamics of a ramjet engine and the steady-state and dynamic performance characteristics of a number of ramjet controls. Three types of engine control systems were investigated: (1) shock positioning, (2) direct control of diffuser-exit pressure, and (3) an optimalizing control designed to obtain peak pressure recovery from the diffuser. Results regarding the engine steady-state performance, engine dynamics, and controls investigations are provided.

Report discussing zero-lift drag data for several bomb configurations at various Mach numbers. Seven configurations were tested with different combinations of interchangeable noses and tail cones with fins, some with different surface conditions. Surface conditions were not found to affect the drag, but the thickness of the tail fins and shape of the noses did change the shape of the drag curve.

"Flight tests were conducted at the NACA Pilotless Aircraft Research Station, Wallops Island, to determine the characteristics of the Allegany Ballistics Laboratory's 6.2inch-diameter Deacon and 10-inch-scale model solid-propellant rocket motors. The tests were performed to assist in the development of these rockets which were designed for, and urgently needed to propel supersonic research models and pilotless aircraft. The tests showed that the rocket motors functioned properly under various flight- acceleration loads over a range of pre-ignition grain temperatures" (p. 1).

"This report describes flight and landing tests made on a group of conventional airplanes. The upward deflection of the elevators was limited to the point where the airplanes could not be made to spin without the aid of power. With the elevator travel thus limited, the airplane in every case had good lateral stability and good aileron effectiveness up to the highest angles of attack which could be obtained in a glide, although this was not true in any case without the limited control" (p. 343).

"Working charts are given for the convenient selection of aluminum alloy propellers of a standard form, to operate in connection with six different engine-fuselage combinations. The charts have been prepared from full-scale test data obtained in the 20-foot propeller research tunnel of the National Advisory Committee for Aeronautics. An example is also given showing the use of the charts" (p. 3).

Report presents the results of wind tunnel tests of the Clark Y, the NACA 23012 and the NACA 23021 airfoils equipped with full-span ordinary flaps and with full-span simple split flaps. The principal object of the tests was to determine the characteristics of the airfoils with ordinary flaps and in addition, to determine the relative merits of the various airfoils when equipped with either ordinary flaps or with simple split flaps. The Clark Y airfoil was tested with 3 widths of ordinary flap, 10, 20, and 30 percent of the airfoil chord.

Report presenting pressure distributions, tuft patterns, and schileren surveys of a sweptback wing-fuselage combination in the 8-foot transonic tunnel at a range of Mach numbers and angles of attack. The wing had 45 degrees of sweepback, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Results regarding an angle of attack of 0 degrees, 4 degrees, 6 degrees, 8 degrees, 12 degrees, and 20 degrees are provided.

Memorandum presenting an investigation of the performances of two annular diffuser designs applicable to turbojet afterburner installations to determine the effectiveness of injection and suction boundary-layer controls. Results regarding inlet measurements, flow observations, static-pressure distributions, downstream velocity distributions, and mean performance coefficients are provided.

Report presenting the effect on base pressure of bleeding air to the semidead-air region at the trailing edge of two-dimensional blunt-trailing-edge airfoils at two Mach numbers. Variation of base pressure with base-bleed rate was determined for two airfoils profiles with both laminar and turbulent boundary layers approaching the trailing edge. Results regarding the effects of jet geometry, effects of jet area, effect of base bleed on the flow in the wake, effect of angle of attack, effect of Reynolds number, correlation of the results with mass-flow rate of the bleed air, and effect of base bleed on the drag of blunt-trailing-edge airfoils are provided.

Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.

Report presenting several short two-dimensional subsonic diffusers over a range of throat Mach numbers from 0.3 to 0.9. The designs incorporated an effective diffusion angle of approximately 30 degrees and an area ratio of 3. At a throat Mach number of 0.7, the resulting profile distortion of the unmodified 30 degree diffuser was diminished from about 11 to approximately 4 percent by using any of the configurations.

Report presenting an analytical study of four combinations of subsonic and supersonic flow in the rotor- and stator-blade passages of axial-flow compressors.

Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.

From Introduction: "This report presents the cooling-air requirements of a "paper" air-cooled turbojet engine operating over a wide range of flight Mach numbers and altitudes. The results are presented for a two-stage-turbine turbo-jet engine having a turbine-inlet temperature of 2500^o R and operating at sea-level static conditions and flight Mach numbers from 0.90 to 2.5 and flight altitudes from 40,000 to 70,000 feet. In addition, the effect of decreasing the blade-inlet cooling-air temperature on the required coolant-flow ratio is presented."

Memorandum presenting an investigation of two-dimensional, supersonic cascade-type inlets at a free-stream Mach number of 3.11. Two cascade-type inlets utilizing different methods of internal-flow compression were designed and tested. Results regarding the cascade inlet and stepped-cascade inlet are provided.