Report presenting a study of the acceleration characteristics of a turbojet engine equipped with variable-position inlet guide vanes in the altitude test chamber. Maximum acceleration values for 3 engines of the same model were also obtained during testing and were found to differ as much as 50 percent. Results regarding the effect of fuel step size and inlet guide vane on acceleration, effect of flight condition, reproducibility of engine acceleration, compressor pressure ratio in relation to acceleration, and acceleration with inlet air distortion are provided.

From Introduction: "The results of an investigation of the low-speed static stability of a simplified model of such an arrangement having one of the airfoils placed vertically on top of the body and the other two as wing panels having negative dihedral are presented in reference 1. In order to provide information for predicting the effects of changes in the basic configuration on the low-speed stability characteristics presented in reference 1, additional measurements have been made."

Report discussing testing on a model of the General Electric P-1 nuclear powerplant to determine its internal aerodynamic characteristics. The main purposes of testing were to measure the mass-flow distribution of air, to measure the total-pressure losses for the duct components and complete model, and to determine modifications necessary to attain the desired performance characteristics.

From Introduction: "The purpose of this paper is to present and discuss skin temperature measurements from two flight tests. Temperature measurements were obtained to a Mach number of 5.4 on the first flight and to a Mach number of 10.4 on the second flight."

From Introduction: "The present paper contains a first-order evaluation of a number of aerodynamic derivatives for a rectangular wing of infinite aspect ratio at finite angles of attack, based upon the linear perturbation theory for rotational flow."

Report presenting the effect of compressibility on the loss characteristics downstream of two-dimensional turbomachine blade rows. In this particular example, increasing the trailing-edge thickness increased the overall loss coefficients significantly, with an effect of compressibility only at exit flow angles close to axial.

Report presenting a method for estimating the equilibrium operating line for a compressor as a component part of a turbojet engine. Charts are presented for locating the equilibrium operating line on the performance map of the compressor component of a turbojet engine operating at sea-level static conditions. Results regarding design-point operation, off-design operation, effect of compressor-discharge bleed, effect of jet-nozzle adjustment, and an example are provided.

Because the Weissinger seven-point results were found to be in error for wings combining high aspect ratio with large amounts of sweep, a simple procedure is demonstrated which corrects errors and results in more accurate span loadings read directly from loading charts. The procedure consists of an alteration of the taper ratio used plus an additional correction applied at the wing root.

Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.

"An investigation was made of a 1/25-scale dynamically similar model of a 255,000-pound transport airplane in order to study its behavior when ditched. The model was free-launched from the Langley tank no. 2 monorail carriage into calm water. Various landing attitudes, flap settings, speeds, and configurations were investigated" (p. 1).

Report discussing several configurations of a swept-wing fighter airplane to determine the effects of modified applications of the transonic and supersonic area rules on the transonic drag-rise characteristics. Information about the lift and pitching-moment characteristics is also provided.

Report presenting an investigation of 2,2,5-trimethylhexane, 2,2-dimethylbutane, and 3-heptane in regards to their susceptibility to vapor-phase oxidation and their oxidation products.

Report presenting testing of heat-treated cast HS-21 turbine blades to determine the effect on the service life by running the blades to failure in a J33-9 turbojet engine. The heat treatment effects were found to depend on the initial structure of the cast blades. Results regarding engine operation, metallurgical studies of as-cast and heat-treated blades, and metallurgical studies of failed blades are provided.

Memorandum presenting the viscosities of slurries containing 50 to 65 percent by weight of boron in JP-5 fuel at temperatures from 30 to 80 degrees Celsius and of slurries containing 50 percent by weight of magnesium in JP-5 fuel from -40 to 80 degrees Celsius. Plastic viscosities of the boron slurries decreased consistently with an increase in temperature. Results regarding boron slurries and magnesium slurries are provided.

Report presenting the effectiveness of a tubular combustor in screening the turbine from foreign objects measured with air flow corresponding to that at static sea-level rated operation. On average, the effectiveness of the production combustor was only 36 percent for the foreign objects introduced in the tests; that is, 64 percent of the objects penetrated the combustor. Results for six different configurations are provided.

Report discussing an investigation to determine the effects of combining auxiliary bleed with ejector pumping on the power requirements and test-section flow of an 8-inch by 8-inch slotted tunnel. Two ejector configurations were used and tests were performed at Mach number range of 0.9 to 1.3. Information about the region of supersonic-flow deceleration, diffuser-inlet Mach numbers, total-power requirements, and which ejector characteristics were preferred is provided .

Report presenting an investigation to show the effects of systematic changes of leading-edge radius, aspect ratio, Reynolds number, and Mach number on the static longitudinal aerodynamic characteristics of sweptback wings in the 19-foot pressure tunnel. Results regarding the effects of leading-edge radius and aspect ratio and effect of Reynolds number and Mach number are provided.

Report presenting an investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the effect of wing sweep on the maximum-lift characteristics of a series of wings having aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections. Testing occurred over a range of Mach and Reynolds numbers. Results regarding lift, drag, and pitching-moment characteristics are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies of a given length and volume but various cross-section shapes were tested at a Mach number of 2.01. The results showed that changes in drag at zero lift due to changes in body cross-section shape from the basic circular shape are small and of the same order as the test accuracy.

Report presenting an experimental investigation to determine the performance characteristics of two side inlets of different shapes. One had a trapezoidal cross section and one was circular and both were fitted with different lips but the same compression ramp. Results regarding pressure recovery, drag, airflow stability, total pressure distribution, and net propulsive force are provided.

Report presenting testing of two low-solidity transonic axial-flow-compressor rotors tested over a range of speeds up to a corrected tip speed of 1000 feet per second to determine the performance of such rotors and to provide experimental rotor blade-element data for low solidity levels. Comparisons of the hub and mean blade-element losses for the three rotors showed that the losses tended to decrease with a decrease in solidity. Results regarding rotor-inlet conditions, rotor-outlet conditions, overall performance, and stall characteristics are provided.

Report presenting the performance increase resulting from the addition of fluorine to the oxygen-JP4 rocket propellant combination evaluated experimentally in a 1000-pound-thrust engine with 0, 30, and 70 percent of fluorine by weight in the oxidant. Maximum specific impulse values obtained were 259, 278, and 287 pound-seconds per pound, respectively, at a combustion pressure of 600 pounds per square inch absolute.

Report presenting a general matrix method for the solution of characteristic-value problems of the type arising in many physical applications. The matrix is applied to the problem of finding criticality and neutron fluxes in a nuclear reactor with control rods. The two-dimensional finite-difference approximation to the two-group neutron-diffusion equations is treated.

Report presenting an investigation using rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack.