Memorandum presenting a linear theoretical analysis of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. It is shown that, with the antenna stabilized in space, the effect of component lags on the response is small, so that the speed of response is small, so that the speed of response can be made to approach closely that of the airframe alone.

Memorandum presenting a linear theoretical analysis made of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. Three guidance systems are compared on the basis of the maximum obtainable speed of response of the missile and guidance-system combination consistent with adequate stability. Results regarding the effect of method of positioning the radar antenna on the speed of response, effect of Mach number on response, and effect of networks are provided.

The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend.

Report presenting an investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine. With water as a coolant, approximately 16 percent of the total propellant and coolant flow was required to film-cool the entire nozzle and with anhydrous liquid ammonia, approximately 19 percent of the total flow was required. Results regarding the coolant results and performance results are provided.

"A method of analysis based on slender-wing theory is developed to investigate the characteristics in roll of slender cruciform wings and wing-body combinations. The method makes use of the conformal mapping processes of classical hydrodynamics which transform the region outside a circle and the region outside an arbitrary arrangement of line segments intersecting at the origin. The method of analysis may be utilized to solve other slender cruciform wing-body problems involving arbitrarily assigned boundary conditions" (p. 1).

Report presenting tests to investigate the use of a simple centering spring, which had no variation of force gradient with impact pressure, as an artificial feel device for the elevator control of a fighter airplane. Testing was conducted using a Chance Vought F4U-4B airplane equipped with power controls. Results regarding the force experienced and effects of the feel system are provided.

"The static longitudinal stability characteristics of a 0.15-scale model of the Hermes A-lE2 missile have been determined in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.98, corresponding to Reynolds numbers, based on body length, of 12.3 x 10(exp 6) to 17.1 x 10(exp 6). This paper presents results obtained with body alone and body-fins combinations at 0 degrees (one set of fins vertical and the other set horizontal) and 45 degree angle of roll. The results indicate that the addition of the fins to the body insures static longitudinal stability and provides essentially linear variations of the lift and pitching moment at small angles of attack throughout the Mach number range" (p. 1).

"A small-scale transonic investigation of two semispan wings of the same plan form was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range of 0.70 to 1.10 and a mean-test Reynolds number range of 745,000 to 845,000 to determine the effects of partial-span leading-edge camber on the aerodynamic characteristics of a swept-back wing. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one, was an uncambered wing and the other had the forward 45 percent of the chord cambered over the outboard 55 percent of the span. The semispan wings had 50deg 38ft sweepback of their quarter-chord lines, aspect ratio of 2.98, taper ratio of 0.45, and modified NACA 64A-series airfoil sections tapered in thickness ratio" (p. 1).

Report presenting an investigation to determine the performance of twin-scoop side inlets mounted on the fuselage of a proposed supersonic aircraft. The inlets had half of a conical spike as the compression surface and a ram-type boundary-layer-removal system. Results regarding the first inlet and redesigned inlet are provided.

Note presenting a consideration of a wing-selection problem sometimes encountered in the preliminary design of supersonic airplanes and missiles. The problem is to determine the span, section thickness ratio, and skin thickness or hollowness ratio of the wing of least drag when the plan form, section shape, wing lift requirement, and flight conditions are assumed known. An example of the application of the method to a diamond wing at Mach number 2.0 for a range of specified flight conditions is presented.

Memorandum presenting an investigation conducted with an NACA submerged inlet at Mach numbers from 1.17 to 1.99. Total-pressure ratio, mass-flow ratio, and static pressure distribution along the ramp and main body were obtained at angles of attack of 0 and 6 degrees for a side inlet location. The results showed that the maximum total-pressure ratio attainable with the submerged inlet decreased from 0.83 at a Mach number of 1.17 to 0.52 at a Mach number of 1.99.

Report presenting information regarding transient oscillations observed in response to elevator pulses of the Douglas D-558-I airplane at a range of Mach numbers and altitudes. An application of the Fourier transform was used to obtain the frequency-response characteristics. The effects of lift coefficient on the frequency response are also included.

"A qualitative investigation of the low-speed directional behavior of a swept planing-tail hull was made in the Langley tank no. 2 in still water and still air with the use of a free self-propelled model. The configuration was directionally unstable over a range of low speed. It was, however, directionally controllable at all speeds by use of the rudder and elevator. Several modifications that were investigated did not improve the controllability" (p. 1).

Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.

Report presenting the effects of approximately 50-percent biaxial stretch-forming on the tensile and crazing properties of polymethyl methacrylate. Results indicated that biaxially stretch-forming polymethyl methacrylate approximately 50 percent does not affect its tensile strength of secant modulus of elasticity in tension. Results regarding standard tensile tests, stress-solvent crazing tests, long-time tensile tests, discussion of mechanism of crazing, accelerated weathering tests, additional experimental work, and possible applications of stretch-forming are provided.

Memorandum presenting an investigation of the rolling effectiveness of a partial-span, perforated spoiler on a wing with 45 degrees of sweepback at Mach numbers from 0.25 to 0.96. The effects of the spoiler on the lift, drag, and pitching moment were also determined. Results regarding Reynolds number, Mach number, and predicted rate of roll are provided.

Note presenting an investigation of the effect of open circular holes on the tensile strength and elongation of sheet specimens of magnesium alloy AM-C52S in both the annealed and hard-rolled condition. Tests were made to study the effect of variable ratio of hole diameter to total specimen width and the effect of spacing and arrangement of the holes.

From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."

From Introduction: "The purpose of this report is to compare the effect on engine performance of the variable-area exhaust nozzle for axial- and centrifugal-flow turbojet engines."

Report presenting testing of two types of solid fuels in a 6.5-inch-diameter ram-jet engine mounted in a free supersonic jet at several Mach numbers. Results regarding radial-burning fuel, end-burning fuel, and a comparison of the two are provided. Unlike in previous testing, no fuel breakup was noted due to recently developed molding techniques.

Report presenting an investigation of a rocket-launched ram-jet engine with radial-burning solid fuel. Results regarding acceleration, altitude, durability of the fuel, net and gross thrust coefficients, and overall fuel specific impulse are provided.

Memorandum presenting an investigation conducted in a modified turbojet engine to determine the cooling effectiveness of an air-cooled turbine-rotor blade employing a corrugated metal sheet brazed to the inner surface of the blade shell to increase the internal heat-transfer area. The corrugated fin blade had a lower integrated average wall temperature at the section investigated than the more promising shell-supported blade types previously investigated. Results regarding the temperature distribution investigation and pressure loss investigation are provided.

Memorandum presenting an investigation of a series of five 75S-T6 aluminum-alloy elementary skin and spar-cap combinations with skin varying from 0.051 to 0.500 inch in thickness to determine the temperature and stress gradients resulting from the application of heat to the surface. The data are presented in the form of tables of the measured temperatures and stresses calculated from the measured strains.

Memorandum presenting the results of a wind-tunnel investigation of the damping in pitch of a model triangular wing with an aspect ratio of 4 combined with a slender pointed body. The investigation was conducted at Mach numbers from 0.10 to 0.95 for Reynolds numbers of 550,000 and 1,250,000 with additional data obtained at Reynolds numbers of 3,000,000 and 6,000,000 at Mach number 0.23. Results regarding the effects of oscillation amplitude, Mach number, Reynolds number, angle of attack, frequency, and pitching axis position are provided.