Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.

Memorandum presenting a performance investigation using hydrogen fuel in a full-scale afterburner conducted with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, grouped by type as concentric ring or radial bar, were investigated at a specified burner-inlet velocity and range of burner-inlet total pressures.

Memorandum presenting an analysis of the effect of adding fluorine to the Vanguard first-stage oxidant. An increase in specific impulse of 5.74 percent may be obtained with 30 percent fluorine. Charts are provided regarding the vehicle performance increases for a zero-drag vertical trajectory.

Pressure tunnel investigation of supersonic store interference in vicinity of 22 degree swept wing fuselage configuration at Mach numbers 1.61 and 2.01.

"Flutter tests have been conducted on two low-aspect-ratio wing plan forms under consideration by the Boeing Airplane Company for the 110A weapons system. These configurations had three heavy nacelles near the trailing edge, and flutter tests were made both with and without the nacelles. Up to a Mach number of 3.0 the dynamic pressure required for flutter of a wing with nacelles was generally higher than that of a wing without nacelles" (p. 1).

Report presenting an investigation of the properties of hydrazine, stability and corrosiveness with a number of construction materials, sensitivity to detonation and temperature, and spontaneous reaction with the oxidants, concentrated hydrogen peroxide, sodium permanganate solution, fuming nitric acid, and tetranitromethane. Results regarding corrosion and stability, sensitivity to temperature and detonation, and theoretical calculations are provided.

"Results of tests of an airspeed head mounted on a freely falling body are presented in preliminary form. Measurements were made throughout the transonic speed range. Details and dimensions of the airspeed head and the body are given in figure 1" (p. 1).

Report presenting a lateral-control investigation of 3- and 6-percent chord spoilers projecting on the upper surface of a wing of high-aspect ratio. The spoilers were found to give large rolling moments at Mach numbers below the Mach number corresponding to the break in the rolling-moment-coefficient curves. Results regarding section pressure distributions, rolling-moment characteristics, normal-force characteristics, pitching-moment characteristics, wing-torsional considerations, and hinge-moment characteristics are provided.

Report presenting tests to determine the effects of sweepback angle and aspect ratio on the drag of an NACA 65-009 airfoil at supersonic speeds. The results indicated that for the range of Mach numbers investigated, increasing the sweepback angle and decreasing the aspect ratio reduced the value of the wing drag coefficient.

Report presenting the air-flow behavior over the wing of an XP-51 airplane including photographs of tufts attached to the wing surface and chordwise pressure distributions. A comparison of tuft studies from flight results are compared with results from wind-tunnel testing. Three types of flow were observed: steady flow, unsteady flow, and break-away flow are provided.

Memorandum presenting an investigation conducted using a single combustor from a 4600-pound-thrust turbojet engine to determine if ignition-plug fouling by carbon deposits could be prevented by retracting the plug from the combustion zone during operation after ignition had taken place. The fuels used were normally conducive to forming carbon. The results indicated that retracting the ignition plug from the combustion zone after ignition prevented plug fouling by carbon.

From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."

The first report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eleven radial stations of the NACA 10-(3)(066)-033 propeller.

Report presenting an investigation using a single combustor from a 4600-pound-thrust turbojet engine to determine the amount of carbon deposition of AN-F-58 fuels and the effect of carbon formations in the combustor on the altitude operational limits. Three fuel blends conforming to AN-F-58 specification were prepared in order to determine the influence of boiling temperature and of aromatic content on carbon deposition. Results regarding carbon deposition and effect of carbon formations on altitude operational limits are provided.

The problems of static and dynamic longitudinal stability both at high speeds and at low speeds are discussed and data are presented which indicate recent progress made in the solution of these problems.

"Low-speed wind-tunnel tests were made of a triangular wing with two arrangements of twin vertical fins. With these twin fins mounted either symmetrically or wholly above the wing chord plane, approximately constant effectiveness in proportion to the fin size was obtained throughout the angle-of-attack range. The addition of these fins, however, resulted in a decrease in maximum lift and a reduction in static longitudinal stability at lift coefficients above 0.4" (p. 1).

Report presenting the performance characteristics of the I-40 jet propulsion engine and an analysis for a range of altitudes and ram pressure ratios. Results regarding the component efficiencies, engine performance, generalizing factors, and windmilling drag characteristics are provided.

Report presenting the performance characteristics of the I-40 jet-propulsion engine for a range of altitudes and ram pressure ratios. Results regarding component efficiencies, engine performance, generalizing factors, and windmilling drag characteristics are provided.

"A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of wings and tail surfaces of arbitrary plan form and stiffness. Provision is made for using either stiffness curves and root-rotation constants or influence coefficients in the analysis. Computing forms, tables of numerical constants required in the analysis, and an illustrative example are included to facilitate calculations by means of the method" (p. 1).

Report presenting the results of an investigation at supersonic speed of the distribution of pressure over the surface of a swept airfoil of biconvex section at various angles of attack. The measurements are compared with supersonic lifting-surface theory, which generally indicated good agreement except over the regions of the airfoil influenced by the subsonic trailing edge and the tips. Results regarding the pressure distribution, boundary-layer studies, and normal force and pitching moment are provided.

Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.

Memorandum presenting a method for approximately determining the minimum moment of inertia of an arbitrarily shaped area, such as the section of a hollow turbine blade. The practical application of the method involves a simple routine tabular procedure.

From Introduction: "The purpose of the present paper is to present results obtained recently relating to the characteristics of a full-span sharp-edge spoiler with an 0.02-chord projection above the wing surface at several chordwise positions and also to the relative effectiveness of the sharp-edge spoiler and a wedge-type spoiler located at the 80-percent-chord line."

Report presenting the results of an investigation on a rectangular ram jet to determine the effect of variation in fuel pressure on the starting characteristics, minimum blow-out limits, combustion efficiencies, gas total-temperature ratio, and net-thrust coefficient. Testing occurred using three different fuel nozzles and over a range of pressure altitudes, airspeeds, and fuel-air ratios.