From Introduction: "The present report gives results at a Mach number of 4.04 of the part of the program concerned with flap controls at Mach numbers from 1.62 to 6.9."

From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."

Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are provided.

Memorandum presenting an investigation of the effects of higher degrees of forming in biaxial stretch-forming of polymethyl methacrylate to about 50-percent strain. Sheets of commercial cast polymethyl methacrylate were hot-stretched approximately 100 and 150 percent, respectively, and tests were conducted on this material and on unstretched cotton material. Results regarding the standard tensile tests, stress-solvent crazing, surface abrasion tests, and x-ray diffraction patterns are provided.

Report presenting an investigation to determine the effects of plan-form taper on the aerodynamic characteristics of a series of symmetrical, unswept wings with thicknesses of 8-percent chord. The wings were tested with four different bodies of revolution over a range of Mach numbers. Results regarding the lift, drag, pitching-moment, lift-curve slope, lift-drag ratio, and pitching-moment curve are provided.

Report presenting an investigation at Mach number 1.61 of the effects of chordwise fences and attached tabs on the hinge-moment characteristics of a half-delta tip control mounted on a 60 degree delta wing. Testing occurred over a range of angles of attack and control deflection. Results indicated that, in general, the effect of fences was to improve the linearity of hinge-moment curves and increase the negative values of slope parameters of hinge moment against control deflection and angle of attack.

Report presenting an investigation in the high-speed tunnel for a range of Mach numbers to determine the lateral control characteristics of a wing-fuselage combination with the wing quarter-chord line swept back 32.6 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 section. Results regarding yawing-moment characteristics, spoiler-slot-deflector testing, and rolling-moment coefficient are provided.

Abstract:"The creep resistance of various uranium binary alloys was investigated at 1500 and 1800 F in vacuum. Tests were made on alloys of uranium with beryllium, columbium, molybdenum, tantalum, titanium, and zirconium and on molybdenum-UO2 composites. Of the alloys examined, those of the uranium-molybdenum system exhibited the best creep resistance. At 1500 F, creep rates of about 0.005%/hr were produced in uranium-molybdenum alloys by a stress of 2500 psi and, at 1800 F, similar creep rates were obtained in composites of 90 wt % molybdenum-10 wt % UO2 by a stress of 12,000 psi."

Report presenting the results of testing of bodies and wing-body combinations by the free-fall method in order to provide information about drag characteristics of airplanes and their component parts at transonic speeds. Two models with a fineness-ratio-12 body of revolution with 45 degree sweptback wings located at different positions were dropped and equipped with improved drag measuring instrumentation and pressure measuring orifices on the portion of the body expected to be influenced by the presence of the wing. Results regarding pressure data and drag data are provided.

The remodeling, fabrication, and instrumentation of a high vacuum system are described. The faults encountered with the old system and their solution are outlined. Tests were made on diffusion pump oils and on the reduction of pump oil back diffusion. The measurement of high vacuum pressures by a cold cathode ionization gage at various points on a vacuum system are discussed.

Report discussing the effects of thermal diffusion length and certain details in the design of light water moderated reactors and their effect on reactivity.

From introduction: "54 tables are given of the Z coefficients."

Report presenting measurements of the intensity of buffeting experienced by the Douglas D-558-II research airplane at a range of Mach numbers. Buffeting was encountered at both subsonic and supersonic Mach numbers and the intensity of the buffeting varied with Mach number and airplane normal-force coefficient.

During the canning of slugs for Production Test 313-105-3-M, a high number of rejects were caused by gas voids in the A1-S1 bonding layer. Since the heat treatment of the slugs in a molten salt bath resulted in a chemically altered surface, an investigation was made to determine the volume of gas evolved from salt-bath heat-treated slugs as compared to other types of slugs. This test was designed as a preliminary test to determine if there were a significant differences.

Photogeologic map of the Orange Cliffs-3 quadrangle, Wayne County, Utah

Plus-minus ratios for pion production by 340-Mev proton bombardment were measured at 13 Mev, 18 Mev, and 42 Mev with the use of the spiral orbit spectrometer.

Abstract: The rate of reaction of oxygen with arc-melted and rolled iodide thorium has been found to obey the parabolic rate law in the temperature range of 850 to 1415 C at 1 atmosphere pressure. The rate constant can be expressed as k = 6 x 10⁷ x e⁻⁶³³⁰⁰/RT cm²/sec. The energy of activation, 63,300 cal/mole, has a probable error of 2,100 cal/mole.

Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. An evaluation of the basic redesign of the compressor and 11 additional modifications are examined.

From Summary: "An investigation of the altitude performance of a 20-inch-diameter high-temperature-ratio ram-jet combustor which had been redesigned to provide good combustor efficiency over a wide range of temperature ratios was conducted at zero angle of attack in a free-jet facility at a Mach number of 3.0. Configurations investigated incorporated a cylindrical control sleeve which confined the injected fuel at low over-all fuel-air ratios to about 40 percent of the engine air flow. This provided an optimum fuel-air mixture over a portion of the flame holder when the over-all fuel-air ratio was about 0.02."

Memorandum presenting an icing investigation conducted to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The overall de-icing characteristics of two of the boots investigated were quite similar. Results regarding boot surface temperatures and general de-icing and runback characteristics are provided.

Report presenting an icing investigation conducted in the icing research tunnel to determine the general de-icing and runback characteristics of three production samples of electric rubber-clad cyclic de-icing boots. The boots were all designed for the same airplane and were designed to operate at the same values of power density, heat-on time, and cycle ratio. Results regarding the boot surface temperatures and general de-icing and runback characteristics are provided.

The following report analyzes whether there is a difference between the neutron streaming in the "armor plate" and 347 stainless steel.

A spectrometer has been used with a hollow prism electrically heated to 70 C to measure the refractive indices of solutions of uranium hexafluoride in bromine trifluoride and uranium hexafluoride in bromine pentafluoride. The refractive indices of the two binary systems have been expressed as a function of composition.

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.