Report presenting an investigation to determine the aerodynamic characteristics of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers operating at positive and negative thrust at a range of Mach numbers when operating at near static conditions. The propellers were operated in combination with a long spinner and at a variety of blade angles.

Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.

Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.

Memorandum presenting an analysis made of the probable range of the stability parameters of present and future missiles. Included is a short review of the dynamic theory and some of the factors and assumptions influencing the stability derivatives and equations of motion.

Report presenting the use of a flush-type electrical pressure cell for measuring rapidly changing aerodynamic forces on a fluttering control surface. The use of the cell is valuable for the measurement of the aerodynamic forces. Results regarding the individual cells, integrated results, resolution of aerodynamic moments, comparison of aerodynamic with inertia moments, and comparison of static and dynamic hinge moments are provided.

"The cooling characteristics of three R-1830-94 engines, two of which were mounted in a test stand and the other in a B-24D airplane, were investigated and the results were compared. The flight tests were made at a pressure altitude of 7000 feet; the test-stand runs were made at ground-level atmospheric conditions. Three cooling runs were made for each engine: variable cooling-air pressure drop, variable carburetor-air flow, and variable fuel-air ratio" (p. 1).

"Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the one with a 7-percent-thick circular-arc airfoil section" (p. 1).

"The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint" (p. 1).

Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.

Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.

"Theoretical calculations of the stability derivatives at supersonic speeds for a high-speed airplane configuration are presented. The range of Mach numbers considered includes those cases for which the wing and tail surfaces have subsonic leading edges, supersonic leading edges, and combinations of the two. The methods of analysis are discussed; these represent detailed consideration of the important effects and contributions of the various airplane components utilizing available theories and theoretically justifiable and reasonable approximations" (p. 1).

From Introduction: "The rolling-pullout maneuver (any maneuver in which rolls occur during high g flight conditions) has been shown to be pertinent to design considerations from the standpoint of the loads produced on a vertical tail (refs. 1 to 3). In order to understand this problem better, the results of an analytical study of effects of large variations of some of the lateral-stability-derivative coefficients on the maximum angle of sideslip at first peak of its oscillation are presented in this paper. Also, expressions for estimating the effects of small variations of or errors in these coefficients on the maximum sideslip angle have been developed and are presented. "

Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduction of adverse effects of propellers on longitudinal stability, and propulsive characteristics are provided.

Investigation of the performance of Inconel 739 (a nickel-base alloy of low critical-element content) buckets in a J33-9 engine showed that Inconel 739 had an engine life at least equivalent if not superior to S-816 buckets operated at 1500 degrees F. Inconel 739 buckets had a small scatter in life and exhibited lower total elongation than S-816. Bucket life was less than that predicted on; the basis of stress-rupture considerations alone. The failure mechanism was probably influenced by fatigue.

From Introduction: "The object of this report is to investigate the effects of after-burner lighting on the engine behavior and control-system requirements of a controlled turbojet engine. In this report, a simulation procedure for the afterburner is developed (based on ref. 3), this afterburner simulation is coordinated with previously developed nonafterburning-engine simulation procedures (ref. 4), and the compensated interacting control systems of references 1 and 2 are used. The results of an analog investigation of the the effects of an afterburner light on several controlled turbojet-engine configurations are reported and evaluated."

Memorandum presenting an investigation conducted in the 27- by 27-inch preflight jet of the release characteristics of a dynamically scaled AVCO booster vehicle, internally carried store model from a scale simulated bomb bay of the B-52 airplane at Mach numbers of 0.64 and 0.93. Simulated altitudes were -11,800 feet and 50,000 feet. Successful releases were obtained at all Mach numbers and simulated altitudes of the test.

"A series of experiments involving the reaction of water with decaborane and HEF-3, a borane fuel consisting mainly of ethyldecaborane, was performed. The results show that the presence of one alkyl group on the decaborane nucleus inhibits the hydrolysis reaction significantly and that the hydrolysis rate can be increased by using an acidic hydrolysis mixture. Two diiododecaborane isomers were prepared for use as intermediates in proposed dimethyldecaborane syntheses, and their melting points, molecular weights, and solubilities in certain solvents were determined" (p. 1).

Report presenting experiments in a 200-pound-thrust jet fuel-nitric acid rocket with an axial-flow igniter employing the hypergolic alkyl thiosphosphite-nitric acid system. No combustion instability was observed in the igniter, but many of the main-stage runs exhibited low-frequency oscillations.

Report presenting the deposition rate of boric oxide from a stream containing submicron particles, which was found experimentally to fit a molecular diffusion equation. Results regarding boundary-layer studies, deposition studies, deposition tests, and turbojet engine performance are provided.

"Efficiency investigations were made on the two-stage turbine from a Mark 25 aerial torpedo to determine the performance of the unit with five different turbine nozzles. The output of the turbine blades was computed by analyzing the windage and mechanical-friction losses of the unit. A method was developed for measuring the change in turbine clearances with changed operating conditions. The turbine was found to be most efficient with a cast nozzle having a sharp-edged inlet to the nine nozzle ports" (p. 1).

Theory and experiment were compared and found in good agreement for the elastic Buckling under combined stresses of long flat plates with integral waffle-like stiffening in a variety of configurations. For such flat plates, 45deg waffle stiffening was found to be the most effective of the configurations for the proportions considered over the widest range of combinations of compression and shear.

Report presenting an investigation of an air-cooled turbine rotor blade consisting of an internal part-span structural strut, corrugated cooling surfaces, and a thin outer shell. The effects on stresses and blade lift of varying strut length, shell thickness, and corrugation dimensions are provided. Testing occurred with the X-40 strut - A-286 shell combination and the S-816 strut - L-605 combination.

Memorandum presenting an investigation of water spray cooling of turbine rotor blades with a representative centrifugal-flow turbojet engine. Water injection from several stationary configurations was investigated in order to determine the most favorable configuration on an overall basis. Results regarding blade temperature distributions, cooling efficiencies of various configurations, rotor blades failures, rotor blade spray patterns, and overall comparison of injection configurations are provided.

In this report the efficiencies of two series of propellers having two types of blade sections are compared. Six full-scale propellers were used, three having R. A. F.-6 and three Clark Y airfoil sections with thickness/chord ratios of 0.06, 0.08, and 0.10. The propellers were tested at five pitch setting, which covered the range ordinarily used in practice. The propellers having the Clark Y sections gave the highest peak efficiency at the low pitch settings. At the high pitch settings, the propellers with R. A. F.-6 sections gave about the same maximum efficiency as the Clark Y propellers and were more efficient for the conditions of climb and take-off.