The effects of fineness ratio (14.2 and 12.2) and boattailing on aerodynamic characteristics of four bodies of revolution at Mach numbers from 1.50 to 1.99 within a range of angles of attack from 0 degrees 10 degrees at an approximate Reynolds number of 35x10(superscript)6 based on body length were investigated. A comparison of experimental data with available theory is included. At zero angle of attack, fineness ratio has no appreciable effect on model characteristics while boattailing and boattail convergence significantly affect fore drag and base drag.

From abstract: General expressions relating product stream compositions to the operating conditions of countercurrent stagewise extraction columns are derived by an inductive method, and the conversion of the general equations to ones involving the particular case of constant extraction factor is demonstrated. For comparison, the derivation of simple column equations by the use of finite difference equations is included.

Introduction: "A limited test progress for the evaluation of type 347 stainless steel pipe which failed the Huey (?) test has been complicated. The tests reported herein were similar in scope to those reported in document number EW-20765, Corrosion Tests on Stainless Steel Plate, Waste Metal Recovery Process. Material tested was obtained on order number EWC-8553, National Tube Company Heat #3X9741. Lots 9789 and 9790."

This report presents "Results of a critical literature review on pressure drop due to isothermal turbulent flow in noncircular geometries" (introduction).

The decontamination of portable instruments by the Calibration Unit has presented a problem for some time. Most of the contamination is in the 100 to 500 c/m or 500 to 2000 d/m range. Higher levels of contamination can usually be reduced to these levels, but further cleaning proves quite difficult

Report presenting combustion-efficiency data for a 5-inch ramjet-type combustor using a simple V-gutter flame holder. Data for homogeneous fuel-air mixtures of 14 pure fuels and 3 fuel blends cover a range of inlet static pressures and velocities.

Report presenting a blade-vibration and rotating-stall survey on a modified version of a production turbojet engine with a 13-stage axial-flow compressor with a design pressure ratio of 7 and an air flow of 120 pounds per second. This testing was carried out due to the problems rotating stall can cause with both experimental and production axial-flow compressors. Results regarding the rotating-stall patterns, rotor-blade vibrations, radial and axial strength of rotating stall, and maximum rotating-stall speed are provided.

Report presenting the effect of adjusting compressor inlet-guide-vane angle on overall compressor performance, stage performance, engine thrust, and specific fuel consumption in a 7000-pound-thrust turbojet engine. Data was obtained at several angles and demonstrated that increasing the guide-vane angle decreased the weight flow at the higher compressor speeds. It had no effect on stage performance other than at the first stage, where it reduced maximum flow, pressure, and temperature coefficients.

The major portion of transfers and inventory in the Chemical Processing Department are dependent on volume measurement. Good volume measurements are therefore essential to good SS material control. Considerable attention has been given to the volume problem especially on primary transfer points. Document HW-57888 discusses the biasing effect pf temperature on manometer oil. HW- 57866 given the procedure for vessel calibration. Other undocumented correspondence has discussed recent calibrations and certain aspects of temperature considerations in the volume determinations. However, there is a need to document for future reference the consideration given temperature and provide at the same time information which covers the temperature angle on all volume methods used in the Chemical Processing Department.

Memorandum presenting an investigation of a 2:1 area ratio conical diffuser of length equal to the inlet diameter with separate variation of several basic parameters for simple nontwisted counterrotating rectangular vortex generators over a considerable range of inlet-boundary-layer thickness. The maximum values of static-pressure rise were determined for angle of attack, spacing, aspect ratio, and span-to-inlet boundary-layer thickness. Results for the diffuser with no vortex generators, effects of selectable vortex-generator variables, effect of inlet-boundary-layer displacement thickness, and use of the maximum indicated vortex-generator design values are provided.

A full-scale turbojet engine was operated with pentaborane fuel continuously for 22 minutes at conditions simulating flight at a Mach number of 0.8 at an altitude of 50,000 feet. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1.3 with JP-4 fuel to 0.98 with pentaborane, a 13.2-percent reduction in net thrust was also encountered. A portion of this thrust loss is potentially recoverable with proper design of the engine components. The boron oxide deposition and erosion processes within the engine approached an equilibrium condition after approximately 22 minutes of operation with pentaborane.

Report presenting a flight-test program investigating a modification to an interceptor system. Results indicate that a significant improvement in the overall response characteristics of the system. The modification minimizes the interaction between the antenna and interceptor motions, which can have a serious influence on flight path stability during a lead-collision attack.

This report provides fundamental equations and maps to calculate neutron behavior in a spherical cavity.

Report discussing methods, advantages, and disadvantages of locating rotating heat exchangers ahead of, within, and behind the main engine compressor. Heat rejection should occur at the compressor discharge for best engine performance. Results regarding turbojet-engine performance, turboprop-engine performance, and a comparison of engine performance with liquid- and air-cooling are provided.

"A general integral form of the boundary-layer equation, valid for either laminar or turbulent incompressible boundary-layer flow, is derived. By using the experimental finding that all velocity profiles of the turbulent boundary layer form essentially a single-parameter family, the general equation is changed to an equation for the space rate of change of the velocity-profile shape parameter. The lack of precise knowledge concerning the surface shear and the distribution of the shearing stress across turbulent boundary layers prevented the attainment of a reliable method for calculating the behavior of turbulent boundary layers" (p. 1067).

The Redox process uses or produces only a very few materials that are hazardous for reasons other than radioactivity. The conditions under which these materials become hazardous were carefully taken into consideration in the development of the process and design of the equipment. A considerable about of information on the hazardous properties of the process materials was obtained so that the pertinent material could be incorporated into the process specifications. Providing the equipment is operating properly and the process is being carried out within specification limits, no hazardous conditions can be created by the process. The purpose of this report is to assemble in a single, readily available document all of the information on the normal concentration limits and safe handling procedures needed to adequately control the use and storage of these materials. This report should be helpful in preparing safety bulletins and provide guidance in case of unusual incidents, malfunctioning of equipment, or contemplated changes in either the process or equipment. It is important to remember that a maximum allowable concentration (MAC) is only a limit on the concentration of a toxic material which cannot be exceeded in the air to which workers are constantly exposed to every working …

During the development of in-reactor corrosion experiments three types of bomb designs have been developed for following quantitatively the consumption of oxygen in a bomb which is fabricated from the particular metal under test. The bombs are designed so as to be rocked continuously during their in-reactor exposure, consequently agitating the uranium salt solution contained in the bomb and permitting gentle movement of the solution past metal specimens and other corroding surfaces. The oxygen pressure is produced within the bomb at the beginning of the run either by the withdrawal of gas from an oxygen tank or by the decomposition of hydrogen peroxide added just prior to closure. Temperature measurements are obtained by mans of thermocouples placed in a well within the bomb body or, in the latest design, there will also be thermocouples staked at several points on the outer wall of the bomb. The assembly is inserted in an experimental access hole in the reactor, brought up to a predetermined operating temperature by means of an electric furnace in close contact with the bomb, and allowed to remain for the desired amount of exposure to reactor radiation. Periodic measurements of temperature and pressure are made and the bomb …

Report presenting the effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap as determined from wind tunnel tests over a range of Mach numbers. Results regarding the section lift and pitching-moment characteristics, variation of lift coefficient with flap deflection, schileren photographs, and effect of angle of attack are provided.

From Summary: "An investigation is being conducted to determine the performance of the 12-stage axial-flow compressor of the XT-46 turbine-propeller engine. This compressor was designed to produce a pressure ratio of 9 at an adiabatic efficiency of 0.86. The design pressure ratios per stage were considerably greater than any employed in current aircraft gas-turbine engines using this type of compressor. The compressor performance was evaluated at two stations."

The stage performance of the X24C-2 axial-flow compressor, as determined from radial distributions of total pressure and temperature measured in each stator-blade row, was investigated at design speed at weight flows corresponding to those of the maximum weight-flow, peak-efficiency, and surge points. The stage performance is presented as the measured stage pressure ratios and the calculated velocity diagrams. The average stage total-pressure ratio at the surge operating condition in the first stage was approximately 1.10; in the second stage, approximately 1.13; and in all remaining stages, approximately constant at a value of 1.15. Regions of inefficient flow are discussed so as to point out the reasons for the poor flow conditions.

Report presents the results of tests made to determine the drag of closed-cockpit and transport-type windshields. The tests were made at speeds corresponding to a Mach number range of approximately 0.25 to 0.58 in the NACA 8-foot high-speed wind tunnel. This speed range corresponds to a test Reynolds number range of 2,510,000 to 4,830,000 based on the mean aerodynamic chord of the full-span model (17.29 in.). The shapes of the windshield proper, the hood, and the tail fairing were systematically varied to include common types and refined design.

Report presenting a highly loaded transonic rotor which was designed, built, and tested as part of a two-stage counterrotating-compressor research program. The design conditions were chosen to explore the upper limits of loading and Mach number for the transonic unit. The complete rotor design procedure is presented as well as the recorded stall traces and techniques for obtaining the data.

Abstract: "The measurement of large, high-frequency, short-pulse currents--ordinarily complicated by inductance, stray magnetic fields, and magnetic forces that tend to disassemble the measuring device--is simplified and made with an average error of 2-1/2% by the use of a specially developed noninductive radial shunt in conjuntion with an oscilloscope. The skin-effect correction is derived theoretically and the accuracy of the method is demonstrated."

In solving the two-group, two medium equations for neutron diffusion in a finite one-dimensional multiplying system, the equations in each medium can be solved, and the boundary conditions used to determine the coefficients. This direct attack involves eight simultaneous linear equations. The opportunities for error are numerous, and, frequently, a great deal of accuracy is lost by subtractions; hence, it is felt that an alternative method of solution, in which numerical errors would be less likely to occur, would be desirable.