An investigation of the performance of a twin-duct air-intake system with a 9 degree compression-ramp inlet mounted on a supersonic airplane in the 8- by 6-foot supersonic wind tunnel at a range of Mach numbers, angles of attack, yaw, and mass-flow ratios. The effect on performance of a series of boundary-layer-removal wedges and a main-duct airflow bypass system were also investigated.

Report presenting an experimental investigation in the 8- by 6-foot supersonic wind tunnel to determine the performance characteristics of a twin-duct side intake system joining into a common duct and utilizing two-dimensional 6 degree compression ramps mounted on a supersonic airplane at Mach numbers 1.5 and 1.7.

Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.

Report presenting free-flight tests made on two pairs of wings of aspect ratio 3.15, taper ratio 0.54, and 45 degrees sweepback in the transonic speed range to measure wing damping and to investigate the possibility of flutter. Results regarding the flight test and analysis and discussion are provided.

Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 to determine the effects of the addition of four small fuselage-mounted cruciform fins on the directional characteristics of a 45 deg swept-wing airplane model at angles of attack up to 15.3 deg and angles of sideslip up to about 16 deg. The results showed that the addition of the four cruciform fins to the model increased the directional stability substantially at the highest angle of attack and, at the same time, caused relatively small changes in drag.

Memorandum presenting oscillatory hinge-moment characteristics obtained from free-flight tests of two rocket-powered models equipped with a 60 degree sweptback clipped delta wing featuring an unbalanced, constant-chord, full-span trailing-edge control. One aircraft had a control with a sharp trailing edge, and the other had a trailing-edge thickness equal to 1/2 the thickness at the hinge line. Results regarding control pulsing systems, control damping, and control restoring moments are provided.

Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.

Report presenting a review of subsonic-diffuser data, which was reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. The report is divided into the following sections: performance at low speeds, the effect of increasing the inlet speed up to choking Mach numbers, illustrations of the effectiveness of boundary-layer controls, and illustrations of the effects of distorted inlet velocity distributions at subsonic speeds.

Thermodynamic properties of hydrogen and its products of combustion with air are tabulated in a form convenient for use in cycle analysis and design of turbojet engines. Only low pressures are considered, and the effects of dissociation are ignored. Several thermodynamic processes are analyzed, and their analysis is illustrated by numerical example.