Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.

"A transonic turbine with a stator trailing-edge thickness reduced from 0.030 to 0.010 inch has been investigated experimentally. The performance results indicated an increase in efficiency of 0.6 of a point at design operation, and as much as 2.4 points at off-design conditions, as a result of reducing the trailing-edge thickness. This improvement could only be partially accounted for by the theoretical change in mixing loss for the two stator-blade rows, and it was felt that the improvement was largely due to a reduced amount of low-velocity fluids entering the rotor and the interference effect of these fluids with the mainstream flow" (p. 1).

Report presenting an investigation to determine the overall performance of the modified eight-stage axial-flow compressor with new fourth-stage stator blades as part of a study of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The performance of the compressor was determined over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed.

Report presenting a low-speed investigation in the free-flight tunnel to provide basic information regarding the effect of frequency on wings oscillating in yaw. The investigation consisted of both free-oscillation tests and forced-oscillation tests of a 60 delta wing, a 45 degree sweptback wing of aspect ratio 2.61, and an unswept wing of aspect ratio 3 over a range of angles of attack. Results regarding the static force test results, directional stability, cross derivative, effective dihedral, and flow separation are provided.

Report presenting the preparation and properties of triethylborane, tri-n-propylborane, and tri-n-butylborane from boron triflouride and the appropriate Grignard reagent. Some of the characteristics examined included the freezing point, heat of fusion, boiling point, heat of combustion, refractive index, density, dielectric constant, and infrared spectra.

Report presenting a study to show the effect of fuel-air ratio and initial temperature on spark-ignition energy and to apply the results to a previously developed theory of ignition. Results regarding initial-temperature effect and fuel-air-ratio effect are provided.

Report presenting an investigation in the high speed tunnel of three missile models with cruciform delta wings swept back 80 degrees and equipped with jet controls to determine the effectiveness of the controls when using ram or mechanically compressed air. Results regarding the rolling characteristics, static rolling-moment coefficients, static pressure, and effect of the location of the jet control are provided.

Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimensional) and Van Driest (two-dimensional), respectively.

The presence of 3 to 5 percent surface-active additive gave the lowest Brookfield apparent viscosity, plastic viscosity, and yield value that were obtained for slurry fuels containing approximately 50 percent vapor-process magnesium in JP-1 fuel. The slurries settled little and were easily remixed. A polyoxyethylene dodecyl alcohol was the most effective of 13 additives tested in reducing the Brookfield apparent viscosity and the yield value of the slurry. The seven most effective additives all had a hydroxyl group plus an ester or polyoxethylene group in the molecule. The densities of some of the slurries were measured.

A study of mixtures of pure methanol and trimethyl borate showed that the composition can be accurately obtained by a simple density determination. The refractive-index determination gives the composition with much less accuracy. The potentiometric titration of boric acid is also discussed.

Performance characteristics of four hydrocarbon fuels having high Btu per gallon were determined in a single turbojet combustor. At simulated low-altitude operating conditions, the fuels with high Btu per gallon generally produced more carbon than did JP-4 and JP-5 fuels. The deposits were reduced appreciably with a fuel-oil additive. At high-altitude conditions, the high Btu-per-gallon fuels gave lower efficiencies than did JP-4 or JP-5 fuels. No attempts were made to improve performance by combustor design modification.

Report presenting a technique and the results obtained of wind-tunnel forced-oscillation tests on a model of the Douglas D-558-II airplane which was instrumented to obtain the dynamic cross derivative and static derivative. Tests were conducted for a range of Mach numbers and angles of attack. Results regarding sample calculations of the period and damping of the full-scale airplane are provided despite not being conclusive due to the inadequate number of flight conditions investigated.

Report discussing an experimental investigation to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. From Summary: "A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration." A large amount of data collected from testing and photographs of the model are provided.

"An experimental investigation has been made n the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration" (p. 1).

Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the chordwise pressure distributions, wing-panel characteristics, wing-section characteristics, and maximum additional normal load on wing leading edge are provided.

Report presenting a supersonic flight investigation of a roll-stabilized acceleration control missile for a Mach number range from 1.4 to 1.7. The control system operation was found to be satisfactory and applicable to some present-day missiles using linear acceleration commands. Results regarding analysis, preflight simulator results, a comparison between simulator and analytical results, flight test results, and a comparison between the flight test and preflight simulator results are presented.

A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 1036 feet per second. The feasibility of using this rotor as a component of an inlet stage of an axial-flow compressor was investigated.

A survey of unclassified axial-flow-compressor literature is presented in the form of brief reviews of the methods, results, and conclusions of selected reports. The reports are organized into several main categories with subdivisions, and frequent references are made within the individual reviews to pertinent material elsewhere in the survey.

Report presenting an investigation in the transonic tunnel to determine the effects of adding external, pylon-suspended stores to a model of the Douglas D-558-II research airplane. Tests were made for two spanwise store locations and covered a range of angles of attack and Mach numbers. Results regarding the drag, lift, and pitching-moment characteristics are provided.

In tests of a portable tank specially designed and constructed under Air Force Contract AF 33(616)-2229, liquid fluorine was safely transported and stored. The investigation included 82 hours of transportation in a total storage time of 2570 hours.

Report presenting the gross weight and uranium investment of nuclear-powered, direct-air, shieldless, ram-jet missiles for a range of altitudes and Mach numbers. Results regarding the effect of reactor operating conditions and flight conditions on ramjet performance and effect of assumptions on ramjet performance are provided.

From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."

A flight test of a rocket-propelled model of the Convair XFY-1 airplane was conducted to determine the lateral stability and control characteristics, The 0.133-scale model had windmilling propellers for this test, which covered a Mach number range of O.70 to 1.12. The center of gravity was located at 13.9 percent of the mean aerodynamic chord. The methods of analysis included both a solution by vector diagrams and simple one- and two-degree-of-freedom methods. The model was both statically and dynamically stable throughout the speed range of the testa The roll damping was good, and the slope of the side-force curve varied little with speed. The rudder was effective throughout the test speed range, although it was reduced to about 43 percent of its subsonic value at supersonic speeds.

Report presenting low-speed testing of the Republic F-105 airplane in the pressure tunnel to determine the plane's lateral control and directional stability and control characteristics. Various combinations of components were tested, including tares, spoilers, ailerons, and wing fences.