Report presenting an investigation in the free-spinning tunnel on a model of the Republic F-105B airplane to determine the spin and recovery characteristics. Results indicated that even with perfect control technique, full movement of the rudder against the spin and of ailerons with the spin is not adequate to ensure satisfactory recovery; extensions of both canard surfaces should accompany the control technique. Results regarding ideal parachute design are also provided.

"Flight tests were conducted on a R-2800-21 engine in the P-47G airplane to determine the effect on the wall temperatures of cylinder 10 of throttling the charge in the intake pipe and of injecting a water-ethanol coolant into the intake pipe. Cylinder 10 was chosen for this investigation because it runs abnormally hot (head temperatures of the order of 45 F higher than those of the next hottest cylinder) at the medium and high-power conditions. Tests with interchanged cylinders showed that the excessive temperatures of cylinder 10 were inherent in the cylinder location and were not due to the mechanical condition of the cylinder assembly" (p. 1).

"The data obtained from cooling tests of an R-2800-21 engine installed in a P-47G airplane were studied to determine which engine and airplane operation variables were mainly responsible for the extremely uneven temperature distribution among the 18 engine cylinders obtained at the medium and high engine-power conditions. The tests consisted of flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The results of the study showed that a flow condition in the induction system associated with the wide-open throttle position, which affected either the fuel air or charge distribution, was primarily responsible for the uneven temperature distribution" (p. 1).

Report presenting flight test data obtained with two Bell X-1 airplanes, one with an 8-percent-thick wing and a 6-percent-thick tail and one with a 10-percent-thick wing and an 8-percent-thick tail. Data was obtained at a variety of Mach numbers, lift coefficients, and test altitudes. Results regarding stick-fixed stability and trim changes are provided.

Report presenting a wind-tunnel investigation of the longitudinal characteristics of a wing-body combination with a wing with leading edge swept back 63 degrees. Lift, drag, and pitching-moment measurements were made over a range of Mach and Reynolds numbers. Results regarding the general characteristics and effect of Reynolds number are provided.

Report presenting a theoretical investigation to determine the effects of autopilot natural frequency on the dynamic performance characteristics of an attitude-controlled supersonic missile configuration with rate damping for a Mach number and altitude range. The autopilots considered were single-degree-of-freedom systems with a fixed damping ratio and various natural frequencies.

"Experimental data have been obtained of the rolling effectiveness of several all-movable wing configurations by means of rocket-propelled test vehicles in free flight. The results are compared with some available methods of estimation. These results validate the use of the simple equation derived by a strip integration and originally presented in NACA RM L50G14b over a wide range of application as a means of estimating the rolling effectiveness of all-movable wings" (p. 1).

"An experimental investigation of the effects of injecting a water-alcohol mixture of 2:1 at the compressor inlet of a centrifugal-flow type turbojet engine was conducted in an altitude test chamber at static sea-level conditions and at an altitude of 20,000 feet with a flight Mach number of 0.78 with an engine operating at rated speed. The net thrust was augmented by 0.16 for both flight conditions with a ratio of injected liquid to air flow of 0.05. Further increases in the liquid-air ratio did not give comparable increases in thrust" (p. 1).

Report presenting an investigation in the free-flight tunnel to study the dynamic stability characteristics at low speeds of a winged tow-target model, the wings of which were free to float about a spanwise axis. Results regarding the wing panels fixed rigidly to the fuselage, wing panels hinged to move together, and wing panels hinged independently are provided.

Report presenting an investigation by means of tests of a flying model in still air to determine the dynamic stability and control characteristics of a delta-wing vertically rising airplane in take-off, landing, and hovering phases of flight. The uncontrolled pitching motion consisted of an unstable oscillation which was more unstable with a rearward than with the normal center-of-gravity location.

Report presenting an investigation in an altitude test chamber to determine criteria for the design of flame holders for a turbojet-engine afterburner. The performance of ten flame holders was obtained in a louvered-liner afterburner operated at constant afterburner-inlet temperature over a range of fuel air ratio and total pressures. Results regarding the effect of gutter cross-sectional shape, effect of gutter width, effect of flame-holder blocked area, effect of trailing and interconnecting gutters, and effect of altitude on V-gutter flame holders are provided.

From Introduction: "An investigation of the variation in turbine-entrance equivalent weight flow for a two-stage turbine equipped with an adjustable turbine stator is presented in reference 1. A general analytical investigation of turbine stator adjustment is presented in reference 2. In reference 2, the effect of stator adjustment on turbine off-design performance is also investigated by analytically computing the performance of a particular single-stage turbine."

Report presenting an extension of NACA RM A52C14 about inlet design and performance for Mach numbers of 1.5 to 2.0. A two-dimensional inviscid analysis is used to compare the performance of several types of inlets when used in conjunction with a turbojet engine with constant-volume air flow. Results regarding air delivery and air requirements, drag factors, evaluation of inlet performance, significance of the drag summation, and inlet and engine-matching considerations are provided.

A study of the effects of variations in lateral-oscillatory characteristics on air-to-air tracking performance has been made, using a conventional, propeller-driven fighter airplane equipped with servo devices for varying these characteristics in flight. Tracking runs were made both in smooth air and in simulated rough air. The lateral-oscillation period, damping, and roll coupling were varied over wide ranges during the investigation.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a body-control arrangement at Mach number 1.61. A 70 degree delta canard-type control mounted in the horizontal plane and with a span-to-body-diameter ratio at the control trailing edge of 2.52 tested both fixed and moving in the presence of a long cylindrical body with a parabolic nose.

Report presenting a low-speed wind tunnel investigation to determine the relationship between the flap effectiveness and the horizontal and vertical position of a partial-span single slotted flap on a sweptback wing-fuselage combination. Results regarding maximum lift, lift increment, and pitching moment are provided.