From Introduction: "The purpose of this report is to compare the effect on engine performance of the variable-area exhaust nozzle for axial- and centrifugal-flow turbojet engines."

Report presenting an investigation of an axially symmetric spike-type nose inlet suitable for a nacelle power-plant installation in the 8- by 6-foot supersonic tunnel at a range of Mach numbers and angles of attack. The inlet was designed to attain a mass-flow ratio of unity a Mach number 2.0. Results regarding the performance of inlet A and inlet B, which differed based on subsonic diffuser area variation, are provided.

From abstract: "This report presents the laboratory development of the MTR-RaLa Process for the production of barium140 from Materials Testing Reactor assemblies." The laboratory studied four possible chemical schemes with the final process being chosen "on the basis of chemical yield and purity of product, ease of recovery of uranium235, simplicty of equipment, and overall time required for processing" (from introduction).

"Graphs have been developed for rapid evaluation of air-induction systems from considerations of their aerodynamic-performance parameters in combination with power-plant characteristics. The graphs cover the range of supersonic Mach numbers to 3.0. Examples are presented for an air-induction system and engine combination of two Mach numbers and two altitudes in order to illustrate the method and application of the graphs" (p. 793).

This report follows a manuscript report made in January 11, 1952, and provides results of a survey that gives corrections as well as suggestions for new and local sources of aggregate material in comparison to the original report. These reports were made in response to a heavy desire of improvement in reactor design and shielding.

Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.

Report presenting an investigation of whether or not a two-stage turbine with the frontal area no larger than the compressor frontal area could be satisfactorily designed to drive a particular compressor under take-off conditions. The low blade-tip speed, high work, and high air flow per unit of frontal area of the compressor make it critical that a two-stage turbine is designed to drive it. Results regarding the effect of work division, effect of variation in cone angle, and effects of radial variations on velocity diagrams are provided.

An investigational drilling project carried out for geological information to determine if several claims near Hite, Utah, warranted an extensive drilling project.

"The solution of heat-transfer problems has become vital for many aeronautical applications. The shapes of objects to be cooled can often be approximated by cylinders of various cross sections with flow normal to the axis as, for instance heat transfer on gas-turbine blades and on air foils heated for deicing purposes. A laminar region always exists near the stagnation point of such objects. A method previously presented by E. R. G. Eckert permits the calculation of local heat transfer around the periphery of cylinders of arbitrary cross section in the laminar region for flow of a fluid with constant property values with an accuracy sufficient for engineering purposes" (p. 223).

Report presenting the application of an aerodynamically pulsed horizontal tail to determine experimentally the longitudinal aerodynamic characteristics of a rocket-powered model in free flight. Results regarding time history, lift and drag, and tail effectiveness and downwash are provided.

Memorandum presenting analyses based on theoretical results of NACA Report 1041 to determine the plan forms of unbalanced trailing-edge flap-type controls with minimum hinge moments due to deflection and requiring minimum work to overcome the hinge moments due to deflection at supersonic speeds. Results of the analyses for longitudinal controls show high-aspect-ratio untapered controls to possess maximum ratios of lift to hinge moment. Results regarding ratios of lift to hinge moment, ratios of lift to deflection work, ratios of rolling moment to hinge moment, and ratios of rolling moment to deflection work are provided.

From Summary: "Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented. Drag data are presented for the Mach number range of 0.3 to 2.9."

Report presenting an investigation in the 8-foot transonic tunnel to determine the effects of twist and camber on the aerodynamic characteristics of a sweptback wing-fuselage configuration. The wing had 45 degrees sweepback of the 0.25 chord, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A-series airfoil sections with 6-percent thickness distribution parallel to the plane of symmetry. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

"Reverse flow theorems in aerodynamics are shown to be based on the same general concepts involved in many reciprocity theorems in the physical sciences. Reciprocal theorems for both steady and unsteady motion are found as a logical consequence of this approach. No restrictions on wing plan form or flight Mach number are made beyond those required in linearized compressible-flow analysis" (p. 253).

From abstract: "A continuous countercurrent solid-liquid contactor has been developed which retains the desirable features of the conventional fixed bed and gains the advantages of countercurrent flow. It can be adapted to many solid-liquid mass-transfer processes such as ion exchange, silica gel adsorption, and ore leaching."

Abstract: "The transformation of metastable beta uranium crystals was found to proceed by a martensitic reaction at room temperature. The features of the transformation of particular interest were that individual uranium martensite plates formed isothermally and grew at a slow rate isothermally."

Indenter gages, Wiancko gages, and interferometer gages were used to measure air overpressure vs time at essentially ground level stations for both the surface (S) and undprground (U) atomic explosions. For the S Burst several instruments were placed on a line extending from an overpressure region of 13 psi to a region of less than one psi. The air measurements for the U Burst ranged from 32 to 2 psi. (D. L.G.)

Report presenting an attempt to improve the part-speed weight-flow-range characteristics of a typical inlet stage by two different approaches. Results regarding the effects of reduction in camber and effects of reduction in guide-vane turning are provided.

Technical report presenting the study of the extent of uranium mineralization on the benches of Shinarump in Temple Mountain.

The chain reacting conditions for plutonium nitrate in water solution have been examined experimentally for a variety of sizes of spheres and cylinders. The effects on the critical mass of the displacement of hydrogen and the addition of poisons to the fuel were measured in water tamped and bare reactors. In this report the data obtained in the investigation is presented graphically and in tables. Some preliminary analysis has been made yielding the results: (i) the absorption cross-section of Pu{sup 240} is 925 {plus_minus} 200 barns and (ii) the minimum critical mass of Pu{sup 239} in water is 510 grams at concentration of about 33 grams per liter.

An estimated minimum critical mass for each of the process vessels in the 231 Building has been calculated on the basis of critical mass data given in the P-11 Project Document HW-24514. The calculations are made assuming the plutonium to be a homogeneous mixture of precipitate and water with some slight neutron poisoning due to other elements. The precipitate is further assumed to have partially settled making an effectively infinite water reflector above the plutonium and hence reducing the critical mass.

Report presenting an investigation to determine the directional characteristics of a sharp-nosed fuselage through a large angle-of-attack range at zero angle of sideslip. The fuselage was found to experience a large increase in yawing moment as the angle of attack increases. The results also indicated that a ring or other roughness used on the nose caused a large decrease in the yawing moment obtained at high angles of attack.

Report presenting an investigation of the aerodynamic loading characteristics of a wing-fuselage combination in the slotted test section of the transonic tunnel. The test was part of a systematic investigation of the effects of varying the amount of sweepback on wings in order to determine their suitability for transonic flight. Results regarding span load characteristics, normal-force characteristics, wing-tip angle of twist, spanwise distribution of section pitching-moment coefficient, pitching-moment characteristics, and fuselage characteristics in presence of wing are provided.

From Summary: "The aeroelastic effects on wing-aileron rolling effectiveness and drag of thin flat-plate delta wings with 45 degree swept leading edge and plain constant-chord ailerons have been investigated. This investigation has been carried out over a Mach number range of 0.7 to 1.6 by means of rocket-propelled test vehicles in free flight. The results show a near-linear decrease in lateral control effectiveness with a decrease in the wing torsional stiffness. An aileron-effectiveness reversal was experienced with the more flexible delta-wing models."