Report presenting wind-tunnel studies of the wake behind eight types of canard control surfaces of equal span mounted on a missile body at Mach number 1.93. The effect of simulated external rocket boosters on the pressure field was also determined for three control-surface plan forms. The investigation also included the effect of end plates attached to the tips of one of the controls surfaces.

Report presenting an investigation at transonic speeds to determine the control characteristics of a linked tab and flap. The control device consisted of an auxiliary lifting surface (tab) mounted on the end of a boom which was linked to a full-span flap. The tab was found to be capable of reducing the flap hinge moment to zero through the angle of attack and Mach number range tested.

Report presenting testing of a 14-inch supersonic mixed-flow rotor of high specific mass flow and an inlet radius ratio of 0.52, which was designed for impulse operation and uniform work output and tested in Freon-12. Results regarding the overall rotor performance, casing friction, entrance flow, distribution of static pressure on the casing, and exit flow are provided.

Report presenting a flight investigation of the variation of the intensity of buffeting with lift and Mach number using a Douglas D-558-II research airplane over a range of Mach numbers and altitudes. Buffeting was encountered during flight at all Mach numbers attained and during level flight at Mach numbers above 0.9. Results regarding the relationship between lift, angle of attack, and buffeting, buffet frequencies, and intensity of buffeting are provided.

Report presenting a wind-tunnel investigation conducted a range of Mach numbers of a 45 degree sweptback wing with varying camber along the span. Two other wings, one with no camber and one with uniform camber, were also tested. Results regarding the wing characteristics and control characteristics are provided.

Memorandum presenting the results of an investigation of control-surface buzz and flutter on four rocket-powered models with a 4-percent-thick unswept wing and 6, 9 and 12-percent-thick 35 degree swept wings with free-floating and statistically mass-balanced control surfaces. The results showed that all of the control surfaces buzzed. The buzz is related to the presence of a shock wave near the control surface for subsonic speeds.

This report summarizes the full-scale engine tests of pentaborane, pentaborane - JP-4 fuel mixtures, and trimethylborate azeotrope fuel. The tests were conducted in a full-scale turbojet engine at a simulated altitude of 50,000 feet and Mach number of 0.08. Engine speeds were 90 to 100 percent of rated speed. Pentaborane reduced the the specific fuel consumption to two-thirds that of JP-4 fuel. However, because boron oxide collected in the engine, the performance deteriorated with continued operation of pentaborane in each of the short-duration tests reported.

Report presenting the X-3 airplane, which has a straight 4.5-percent-thick wing of modified hexagonal section, which has been flown to maximum wing normal-force coefficients in the Mach number range from 0.7 to 1.1 at an average altitude of 30,000 feet. Measurements were made of airplane and wing-panel maximum normal-force coefficients and of some buffeting characteristics.

A limited exploratory investigation of the rate of coking of four JP-4 fuels in electrically heated metal tubes was conducted in order to provide design information for fuel prevaporizers for turbojet-engine combustors. The fuels tested included two production and two minimum-quality JP-4 type fuels. The heating tube was operated at fuel pressures of approximately 500, 400, and 50 pounds per square inch. The operating fuel temperature was varied between approximately 600 degrees and 1200 degrees F.

Report presenting testing of three wings of different aspect ratios at a range of angles of attack to provide information on the effects of large angles of attack on the lift and normal force on triangular wings in a specific Mach number range. Results regarding the comparisons with data from semispan tests, prediction of lift and normal force and comparison with the experiment, and maximum lift coefficient are provided.

Report presenting an experimental investigation to determine the effects of vertical location of an unswept wing and horizontal tail on the aerodynamic characteristics in pitch of a wing-body-tail combination. The wings had an aspect ratio of 3.09, a taper ratio of 0.39, the quarter-chord line swept back 11.5 degrees, and biconvex sections.

Report presenting an experimental investigation of a high subsonic Mach number turbine with high suction-surface diffusion. The subject turbine was designed for a high weight flow per unit frontal area, a high specific work output, and a relative critical velocity ratio of 0.82 at the rotor hub inlet.

Experimental study of effects of combustion roughness and controlled mechanical oscillations on diffuser operation was conducted on an 8-inch ram jet at Mach number 1.87. Within experimental accuracy, the optimum mean combustion-chamber static pressure occurred when the maximum instantaneous static pressure equalled the optimum steady-flow value and the corresponding decrement in optimum mean static pressure was equal to one-half the total amplitude of the pressure pulsations. A marked attenuation of amplitude of cold-buzz pressure fluctuations was effected over limited range of subcritical diffuser operation by means of properly tuned rotating disk located in combustion chamber.

Report presenting tests of an airplane model equipped with missiles to investigate the capability of that combination to achieve satisfactory launching and jettisoning of the missiles. Information about pylon modifications, missiles in launch positions, missile trajectory, and missiles in jettison positions is provided.

Memorandum presenting a high subsonic Mach number turbine with high suction-surface diffusion investigated experimentally. The subject turbine was designed for a high weight flow per unit frontal area, a high specific work output, and a relative critical velocity ratio of 0.82 at the rotor hub input.

Report presenting summaries of full-scale engine tests of pentaborane, pentaborane-JP-4 fuel mixtures, and trimethylborate-methyl-alcohol-azeotrope fuels. Tests were conducted at an altitude of 50,000 feet and Mach number of 0.8. Results regarding the fuel effects on overall performance, effects on component performance, effect of turbine-outlet temperature on engine performance, and miscellaneous observations are provided.

Supersonic performance of variable two-dimensional inlets designed for engine-inlet matching.