From Introduction: "In the present paper, calculations are presented to show the relative effects of wide variations in the roll performance and normal-accleration capability. Brief analyses are also included to show the effect on the success of attacks of other design factors such as speed and radar range."

Memorandum presenting several proposed-high performance aircraft that have been studied analytically and by model flight tests to define some problem areas in dynamic lateral behavior of high-speed aircraft which require specific attention. Aileron control problems and Dutch roll characteristics with and without artificial damping were considered.

Report presenting a study of several proposed high-performance aircraft to define some problem areas in dynamic lateral behavior of high-speed aircraft which require specific attention. Aileron control problems and Dutch roll characteristics with and without artificial damping were explored in depth.

Report presenting an investigation of an all-internal conical compression inlet with annular bleed at the throat at Mach number 5.0 and zero angle of attack. Results regarding the performance of the diffuser alone, a Pitot-pressure survey of the flow leaving the diffuser, total-pressure distribution, and inlet efficiencies are provided.

From Summary: "An all-internal conical compression inlet with annular bleed at the throat was investigated at Mach 5.0 and zero angle of attack. The minimum contraction ratio of the supersonic diffuser, coincident with a mass-flow ratio of 1.0, was determined to be 0.084 as compared with the isentropic contraction ratio of 0.04 at Mach 5.0. The over-all inlet performance was very sensitive to the amount of annular bleed at the throat because of the extensive boundary layer."

Report presenting an investigation in the full-speed tunnel to determine the low-speed stability and performance characteristics of a model of a jet-powered airplane configuration capable of vertical takeoff and landing with engines in a tiltable low-aspect-ratio wing. Static longitudinal and lateral characteristics were obtained for various angles of attack, wing tilt angles, and thrust coefficient suitable for takeoff and landing.

Memorandum presenting an investigation in the supersonic pressure tunnel to determine the stability and control characteristics of two canard airplane configurations equipped with various sizes of canard control surfaces. Two wings of equal area but differing in plan form were provided. Results regarding longitudinal characteristics and lateral characteristics are provided.

Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air.

Report presenting an investigation in the supersonic pressure tunnel to determine the effects of various vertical positions of a wing and horizontal tail on the static longitudinal aerodynamic characteristics of a trapezoidal wing model. Results regarding effect of wing vertical position and tail-on characteristics are provided.

From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The stream static pressure is maintained at about 1 atmosphere, the free-stream temperature at about 75^o F, and the stagnation temperature at approximately 500 ^o F (ref.1)."

"An analog computer study was made in order to investigate the inertia coupling in rolling maneuvers of an airplane configuration utilizing a variable-incidence wing for longitudinal control. A five-degree-of-freedom system of equations was used, and only one set of flight conditions was included in this study. The results, when compared to those for a conventional tail-control airplane, indicated significant advantages for the variable-incidence-wing type of control in reducing undesired dynamic effects during rolling maneuvers" (p. 1).

An investigation of the burning rates of single drops of 15 hydrocarbon and nonhydrocarbon fuels in quiescent air at room temperature and pressure. The drop burning rates were found to be proportional to drop diameter. The experimentally determined drop burning rates were in orderly agreement with those predicted by theoretical analysis, but the absolute values differed significantly.

"The addition of fuselage volume, concentrated on top of the forward portion of the fuselage, for the purpose of delaying the drag-rise Mach number of subsonic airplanes at lifting conditions is investigated. The additions have been designed on the basis of the area rule and other important considerations to provide greater practicability of application compared with shapings previously investigated. The addition delayed the drag-rise Mach number by an increment of approximately 0.03 for a configuration having a wing with moderate thickness and 35 deg of sweepback at a lift coefficient of 0.3. A lesser delay was obtained for a configuration with a thicker wing. The additions increase the nonlinearities of the variations of pitching moment with lift" (Abstract).

Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane in the transonic tunnel. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.

Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane. The amplitude and frequency of pressure fluctuations were measured using an electrical pressure gage mounted on the diffuser wall at several Mach numbers and mass-flow ratios. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.

"A two-dimensional wind-tunnel investigation of the flow and force characteristics of four NACA 6A-series airfoils with thickness ratios of 4, 6, and 9 percent has been conducted in the Langley airfoil test apparatus at at transonic Mach numbers between 0.8 and 1.25. The Reynolds number range for these tests varied from 2.6 x 10(6) to 2.8 x 10(6). As was expected, the airfoils exhibited a smooth transition in force coefficients from a Mach number of 1.0 to the values obtained at the higher speeds. Lift-curve slope and maximum lift-drag ratio correlated very well on a basis of the transonic similarity laws at Mach numbers above 1.0, but below that value the correlation was not good" (p. 1).

The static longitudinal and lateral stability characteristics of an 0.065-scale model of the XRSSM-N-9a (REGULUS II) missile at Mach number range of 1.6 to 2.0 at a Reynolds number per foot of 2.0(exp 8).

Turbine centrifugal stress is a limiting factor for all flight conditions studied. This stress is more severe for sea-level operations than for subsonic flight at the tropopause. Turbines designed for a stress of 30,000 psi are capable of driving a light, compact, high-spedd compressor but only at high values of specific fuel consumption. An increase in turbine-inlet temperature is accompanied by an increase in turbine centrifugal stress.

Memorandum presenting an investigation conducted to reduce the pressure drop in an experimental combustor designed to operate with high efficiencies at high altitude. The combustor utilized a previously designed prevaporizing fuel system that supplied vapor fuel to the injectors for high-altitude operation. Results regarding combustor development and performance of final combustor model 47L are provided.

An annular prevaporizing turbojet combustor having pressure losses lower than those obtained in current turbojet combustors was developed, Pressure losses of 2 to 4 percent, satisfactory temperature profiles, and combustion efficiencies of 98, 88, and 81 percent were obtained at 56,000, 70,000, and 80,000 feet respectively, for a simulated 5.2- pressure-ratio engine at rated speed and 0.6 flight Mach number with JP-4 fuel. Use of JP-5 fuel resulted in a small penalty in efficiency due, at least in part, to insufficient prevaporizer capacity.

Report presenting a method to provide a simple means of comparing engine components on the basis of either range or the margin of thrust over drag. The equations include the variation in thrust coefficient and specific impulse and the change in engine weight and drag. Four general cases are considered: fixed-size airplanes with constant gross weight, fixed-size airplanes with variable gross weight, variable-size airplanes with constant payload weight, and variable-size airplanes with constant ratio of payload to gross weight.

Report presenting analytical estimates of the thrust, efficiency, drag, and weight of the air-turborocket engine. The effects of changes in the engine components on design and off-design performance are emphasized. Results regarding the performance, effect of design parameters, effect of subsonic cruising Mach number, geometry variations, engine weight estimates, and comparison with turbojet engines are provided.

Report presenting an evaluation of data obtained with an automatic constant inlet-pressure control valve designed to facilitate the study of transient engine performance characteristics in the altitude wind tunnel. The engine characteristics obtained by use of the pressure valve were compared with those obtained with a bellmouth inlet operating in simulated free-stream conditions.

Memorandum presenting a study of several typical air induction systems for modern aircraft, which indicates that flow distortions of about-pipe-flow magnitudes can be expected at near-optimum inlet-engine matched air-flow conditions and at small angles of attacks. The distortions may be seriously increased by operation at large angles of attack or yaw, or by supercritical operation of the inlets. Boundary-layer bleed, duct overexpansion and contraction, and freely rotating fans appear promising as devices for reducing distortions with little cost in propulsive thrust.