From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."

Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.

Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.

Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for four airplane-like configurations determined from tests at a range of Mach numbers and angles of attack. The wings and nose shapes were modified for each of the configurations.

Memorandum presenting hypothetical two-spool nuclear-powered turbojet engines with sea-level static design compressor total-pressure ratios of 20, 15, and 9 and total-pressure losses between the inner-spool compressor exit and turbine inlet of 10 and 30 percent. Results regarding compressor operating lines, gas-generator performance, engine performance, and some general remarks are provided.

Report discussing an investigation to determine the free-jet performance characteristics of the XRJ43-MA-3 20B3 ram-jet engine at a Mach number of 2.70 at several angles of attack, inlet temperatures, and fuel-air ratios. Information about the inlet supercritical mass-flow ratio, diffuser-outlet Mach number contours, and effect of angle of attack and inlet temperature on engine performance is provided.

Report presenting the results of oscillation tests to measure the dynamic-rotary stability derivatives of an airplane model at high subsonic speeds. Measurements taken included the damping in pitch, damping in yaw, damping in roll, and the yawing moment due to rolling velocity.

Memorandum presenting a review of some of the analytical and experimental studies of the use of liquid hydrogen as a jet-engine fuel and which show the possible extension of aircraft performance that will follow adequate research and development effort on the problem of its use.

Report presenting an investigation to determine the effects of taper ratio and body indentation on the aerodynamic loading characteristics of a 45 degree sweptback wing in the presence of a body in the transonic pressure tunnel for a range of Mach numbers and angles of attack. Results regarding the effect of wing-body-juncture seals, general effects of the variables, effect of taper ratio, effects of body indentation, and comparisons with other data are provided.

The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined.

Report presenting an investigation to determine the effect of outer-shell design variables on the internal performance characteristics of plug-type nozzles designed for a pressure ratio between 6 and 12. Inlet Mach number and outer-shell angle were found to have no effect on nozzle thrust coefficient. For choked flow, the effective throat area decreased when the inlet Mach number or outer-shell angle was increased.

A tank investigation was made of the hydrodynamic characteristics of a 1/13.33-scale jet-powered dynamic model of the 160,000-pound Martin XP6M-1 flying boat. Longitudinal stability during take-off and landing, resistance of the complete model, spray characteristics, flap loads, and effect of sinking speed in smooth and rough water are presented, as well as behavior during taxiing, take-off and landing in rough water. The effect on spray of two bows and several bow-spray-strip modifications and the effect on resistance of afterbody chine strips also are presented.

Report presenting an investigation to obtain the effects of a 20-percent-semispan all-movable wing-tip control on the longitudinal stability characteristics of a twisted and cambered 60 degree sweptback-wing-indented-body configuration. Testing occurred over a range of angles of attack and Mach numbers. Results regarding the effects on drag coefficient and lift-drag ratio are also provided.

Memorandum presenting the effects on combustor performance of operation at the high inlet-air pressures, temperatures, and velocities representative of conditions that may be encountered in high-pressure-ratio turbojet engines or at high flight speeds studied in a single tubular combustor. Some of the performance characteristics investigated were combustor-liner temperatures, carbon deposition, smoke formation, and combustion efficiency.

Data obtained from the first flight test of a ram jet utilizing a magnesium slurry fuel are presented. The ram jet accelerated from a Mach number of 1.75 to a Mach number of 3.48 in 15.5 seconds. During this period a maximum values of air specific impulse and gross thrust coefficient were calculated to be 151 seconds and 0.658, respectively. The rocket gas generator used as a fuel-pumping system operated successfully.

Report presenting performance testing of a supersonic compressor designed for a tip speed of 1400 feet per second, a pressure ratio of 2.0, and a corrected weight flow of 30.5 pounds per second. The overall performance results of the rotor alone at design speed gave a pressure ratio of 2.17, an adiabatic efficiency of 89 percent, and a weight flow of 28 pounds per second. A comparison with the predicted design results is provided.

Report presenting an investigation of the boattail pressures and base pressures of two twin-jet afterbody configurations at Mach number 1.91. They were designed as a simple merging of two blunt-based conical afterbodies with spacings of 1.4 and 1.7 jet diameters between the jet center lines. Results regarding support-strut interference, effect of jet spacing ratio, effect of jet exit angle, longitudinal boattail pressure distribution, circumferential pressure distributions, and effect of a reflection plane are provided.

Report presenting an experimental investigation to determine the effect of rotor leading-edge sweepback on the aerodynamic performance of a transonic turbine. Using an unmodified stator with the modified rotor resulted in large incidence angles at the rotor mean and tip sections.

Report presenting zero-lift experimental flutter data in a range of Mach numbers on a 1.5-percent-thick, untapered, unswept, solid steel wing with hexagonal airfoil sections and wing length-to-chord ratios of 1.61 and 1.73. The wing was tested as a cantilever with and without a half-body-of-revolution fuselage. Results regarding the calculated flutter speeds and frequencies, effect of fuselage, variation of wing flutter characteristics with Mach number, results of analytic solutions, and variation of wing flutter characteristics with mass ratio are provided.

From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."

Report presenting flutter data over a range of Mach numbers in free-flight testing of several wing-body combinations as part of a general zero-lift drag investigation. The wings all had the same streamwise airfoil sections and the plan-form variations consisted of delta wings, diamond wings, and an arrow wing. Time histories of model speed, Mach number, and air density are provided for each model as well as flutter frequency, amplitude, and reduced-frequency parameter plotted as functions of model speed.

Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel at several free-stream Mach numbers for a range of primary-nozzle pressure ratios and secondary weight-flow ratios to determine the effects on performance of varying the ejector diameter ratio by simulated iris flaps. Results indicated that increases in ejector gross force and secondary-to-primary total-pressure ratio were obtained subsonically when diameter ratio was reduced, thus reducing overexpansion losses.

Report presenting testing of a model of a supersonic airplane configuration with a 40 degree sweptback wing with circular-arc sections at Mach numbers 0.85 and 1.15 to obtain lateral stability data at low lift and to evaluate the test and analysis technique. Results regarding time history, trim characteristics, amplitude ratio and phase of rolling angular acceleration to angle of sideslip, sideslip derivatives, moment derivatives due to yawing, and a comparison of present data with previously obtained data are provided.

Memorandum presenting performance investigations of 13 fuels - five hydrocarbons, four oxygenated hydrocarbons, and four substituted hydrocarbon-type fuels - conducted in a single tubular turbojet combustor in order to determine a possible relation between combustor performance and fuel properties. Combustor temperature rise and combustion efficiency were determined at a variety of air-flow rates, inlet-air total temperatures, and a range of heat-input values.