Jet engine induction systems investigations and relationship of air inlets, drag, airframe, pressure recovery, flow and interferences.

Report presenting an investigation to evaluate the engine service performance of nozzle-diaphragm blades of AISI 321 and AISI 347 stainless steels. Data were obtained from three nozzle diaphragms alternately bladed with each of the two materials. Results regarding a visual inspection, a metallurgical examination, the mechanism of cracking, and the classification of failures are provided.

A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.

The performance of MIL-F-5624A fuels, grades JP-3 and JP-4, was investigated in an axial-flow turbojet engine over a range of altitude conditions of 10,000 to 55,000 feet. Examination of the fuel flow, combustion efficiency, and net thrust specific fuel consumption showed the grade JP-4 fuel to be slightly inferior to the grade JP-3 fuel, although the altitude ignition limits were essentially equal for the two fuels over a range of flight Mach numbers and fuel-inlet temperatures.

From Introduction: "It is the purpose of this report to assemble principles of induction-system design for flight to a Mach number of 2 and to use existing data to show the consequences of compromising them."

Report presenting an investigation at two Mach numbers for a range of Reynolds numbers to determine the pressure distributions at several spanwise stations for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. The report contains the tabulated pressure data for the complete range of test variables.

Report presenting an investigation on a body of revolution with a sweptback wing with a 0.25-mean-aerodynamic-chord point at the maximum body diameter and 1.2 mean aerodynamic chords behind the maximum diameter. The fuselage had a fineness ratio of 10, a 45 degree swept wing with an aspect ratio of 4.0, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Lift, drag, pitching moments, and angles of attack were measured at a range of Mach numbers.

A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.

Report presenting an investigation to determine the combustion characteristics of pentaborane and diborane in a turbojet combustor. Four different test conditions were explored, which varied in inlet total pressure, temperature, and simulated flight conditions. Results regarding the combustor itself and performance of diborane fuel at high altitude are provided.

Metal temperatures were obtained on a full-scale ejector nozzle installed on an afterburner operating at exhaust-gas temperatures up to 3450 degrees R. A favorable afterburner-outlet temperature profile helped keep the primary-jet nozzle components cool. The ejector shroud temperatures were much more sensitive to secondary airflow than were temperatures on the primary-jet nozzle.

From Summary: "The spray flammability limits of various high-energy fuels and hydrocarbon fuels were determined experimentally in an apparatus which measured the minimum percent of oxygen by volume that would permit the ignition of a particular fuel. The fluids investigated were ethyldecaboranes, aliphatic hydrocarbons, olefins, aromatic hydrocarbons, and esters."

Report presenting a flight investigation of a swept-wing fighter-type airplane to determine drag coefficients, longitudinal and lateral stability derivatives, effects of aeroelasticity on rolling effectiveness, and the effect of the engine jet exhaust on the trim characteristics over the range of Mach numbers.

Report presenting a comparison of three centrifugal impellers with parabolic, circular, and skewed-parabolic blading that were modified using a recently developed design procedure to reduce velocity gradients along the hub from inlet to outlet. All of the original dimensions except for the shroud contours were retained. Results regarding a comparison of the original and modified parabolic-bladed, circular-bladed, and skewed-parabolic bladed impeller are provided.

NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the acceptance tests conducted by the Northrop Aircraft Corporation. This report presents data obtained on the stalling characteristics of the airplane in the clean and gear- down configurations. The center of gravity was located at approximately 18 percent of the mean aerodynamic chord during the tests. The results indicated that the airplane was not completely stalled when stall was gradually approached during nominally U accelerated flight but that it was completely stalled during a more abruptly approached stall in accelerated flight. The stall in accelerated flight was relatively mild, and this was attributed to the nature of the variation of lift with angle of attack for the 001-614 airfoil section, the plan form of the wing, and to the fact that the initial sideslip at the stall produced (as shown by wind-tunnel tests of a model of the airplane) a more symmetrical stall pattern.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Whether the Civil Air Patrol is exempt from the payment of the license fee for motor vehicles under the provisions of Article 6675 A-3, V.A.C.S.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Applicability of the Occupation Tax levied by Section 31, Article 7047, Vernon's Annotated Civil Statutes, to rodeos promoted or produced by specific sponsors.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Sale of personal stock of officers and directors of an insurance company and the duty owed by such officers and directors to the insurance company.

To determine the safety of the array in the storage vault for the SM-2 experimental fuel plates, two criticality criteria were applied. A maximum of 18 fuel plates was stored in sthainless steel tubes and the tubes belted to a frame on the wall to prevent movement. No tube could go critical by itseIf. The vauit was then assumed completely flooded by water. In the first calculation, the fuel array was assumed to be distributed uniformly over the wall forming a large slab. This method indicated the array might be critical if the steel tube and cadmium lining were neglected. In the second method, a conservative calculation, wnich included the steel tube and cadmium lining was made. This method indicataed the array was subcritical. Calculations were then made of the criticalty of the SM-2 vault without the steel--cadmium tubes and wcoden blocks. The multiplication factor of the vault was also calculated. In order to determine the accuracy of these calculations, an ORNL critical experimental array was calculated applying the same analytical techniques. (M.C.G.)

A fuel-cycle economic study was made for a 315-Mw(e) graphite-moderated U/sup 235/-Th-fueled fused-salt reactor. Fuel cycle costs of approximately 1.3 mills/kwh may be possible for such reactors when reprocessed for U/sup 233/ and U/ sup 235/ recover y at the end of a 9-year cycle. Continuous removal of fission products during the reactor cycle does not appear to offer any great economic advantage for the converter reactor considered. (auth)

The rate of oxidation of chromium(III) to chromium(VI), catalyzed by ruthenium, was determined at various temperatures and oxygen concentrations. The rate at 300 deg C was too rapid for measurement by aliquot sampling. In the temperature range of 225 to 275 deg C, oxidation was rapid and the rate increased with oxygen concentration. A linear dependence of initial oxidation rate on the reciprocal of chromium(VI) concentration suggested that a rate-controlling step in the reaction mechanism may be desorption of chromium(VI) from the ruthenium catalyst. The activation energy calculated for the reaction is 19 kcal/mole. (auth)

Using the 1.19-Bev/c antiproton beam recently discovered at the Berkeley Bevatron of the University of California, we have measured the attenuation cross section in beryllium and copper. These cross sections are compared to attenuation measurements made with the same geometry using positive protons of the same incident energy (497 MeV).

Varying amounts of radiation decomposition during storage in the dry form have been found in the cases of C{sup 14}-labeled valine, norvaline, norleucine, choline chloride, calcium glycolate and cholesterol. These data indicate that investigators using labeled organic compounds should make frequent checks of the purity of these compounds in order to exclude the possibility of the presence of decomposition products.

A considerable volume of work was accomplished during the past three months in the tracer program, experiments being conducted with At{sup 211}, carrier-free Bi{sup 206}, carrier-free Mn{sup 52}, carrier-free Mo{sup 93,99}, Np{sup 237}, Ta{sup 182} of a fair degree of specific activity, carrier-free Sc{sup 46}, and high specific activity Tm{sup 170}.

The existence of antiprotons has recently been demonstrated at the Berkeley Bevatron by a counter experiment. The antiprotons were found among the momentum-analyzed (1190 Mev/c) negative particles emitted by a copper target bombarded by 6.2-Bev protons. Concurrently with the counter experiment, stacks of nuclear emulsions were exposed in the beam adjusted to 1090 Mev/c negative particles in an experiment designed to observe the properties of antiprotons when coming to rest. This required a 132 g/cm2 copper absorber to slow down the antiprotons sufficiently to stop them in the emulsion stack. Only one antiproton was found in stacks in which seven were expected, assuming a geometric interaction cross section for antiprotons in copper. It has now been found that the cross section in copper is about twice geometric, which explains this low yield.