Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.

Technical report. Areas covered are properties of uranium halides, properties of uranium nitrides, and hydride formation at high pressure.

Memorandum presenting an investigation to determine the effects of jet exhaust and Reynolds number on the flow over the vertical stabilizer and rudder of the Douglas D-558-II research airplane with special attention to an understanding of the rudder reversals experienced in flight on the full-scale airplane. Tests were made at Mach numbers of 1.62, 1.93, and 2.41 over a range of ratios of jet static pressure to stream static pressure from the jet-off ratio to about 40 and for a maximum range of sideslip angles of 6 degrees. Results regarding the effect of varying jet static-pressure ratio, effect of varying sideslip angle, effect of varying Reynolds number, and effect of varying angle of attack.

Memorandum presenting a study of the effects of automatic augmentation or controlling systems on the tail loads experienced in rolling maneuvers and in pitch-up. The results were calculated on an analog computer and the equations of five degrees of freedom were used for the rolling maneuvers and three degrees of freedom for pitch-up.

Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.

Memorandum presenting an investigation conducted in the supersonic wind tunnel on a 16-inch ramjet that was equipped with an afterburner and used gaseous hydrogen for both the primary and afterburner fuels. The primary nozzle had a contraction ratio of 0.6 while the exit nozzle had a contraction ratio of 0.9. Data were obtained at a free-stream Mach number of 3.0 and zero angle of attack.

Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine the total-pressure recovery obtainable at Mach number 1.85 with a shock diffuser with projective cones designed to produce two oblique shocks ahead of the diffuser inlet. The variation of total-pressure recovery with tip projection was investigated for four cones with different included angles. A maximum total-pressure recovery of 94.5 percent was attained with the best configuration at an angle of 0 degrees.

Report presenting an investigation of the variables pertinent to the control of gas temperatures of gas-turbine engines during starting conducted by obtaining time records of the variables involved during actual starting conditions. Poor control of gas temperatures during starting was found to be caused by an accumulation of fuel in the engine before ignition and excessive fuel-flow rates at the time of ignition.

Report presenting the design and performance of a turbine to drive a supersonic compressor in order to determine the problems that would be encountered in turbines required to drive high-speed, high-weight-flow compressors. A model of the turbine was built and operated over a range of speed and total-pressure ratios. Results regarding performance, the effects of rotor choking, and possible modifications to the design are provided.

Report presenting an investigation of internal film cooling of the exhaust nozzle of a 1000-pound-thrust liquid ammonia liquid-oxygen rocket engine. With water as a coolant, approximately 16 percent of the total propellant and coolant flow was required to film-cool the entire nozzle and with anhydrous liquid ammonia, approximately 19 percent of the total flow was required. Results regarding the coolant results and performance results are provided.

Report presenting pressure and temperature changes in the cooling air flowing through air-cooled gas-turbine blades, which have been measured experimentally in a static cascade on a 10-tube blade for isothermal and nonisothermal flows, and on a 13-fine blade for isothermal flows. Values of pressure and temperature were obtained for a range of cooling-air flows over a range of Reynolds numbers, Mach numbers, and heat-transfer rates.

Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.

From Summary: "A series of publications on the source-distribution methods for evaluating the aerodynamics of thin wings at supersonic speeds is summarized, extended, and unified. Included in the first part are the deviations of: (a) the linearized partial-differential equation for unsteady flow at a substantially constant Mach number. b) The source-distribution solution for the perturbation-velocity potential that satisfies the boundary conditions of tangential flow at the surface and in the plane of the wing; and (c) the integral equation for determining the strength and the location of sources to describe the interaction effects (as represented by upwash) of the bottom and top wing surfaces through the region between the finite wing boundary and the foremost Mach wave. The second part deals with steady-state thin-wing problems. The third part of the report approximates the integral equation for unsteady upwash and includes a solution of approximate equation. Expressions are then derived to evaluate the load distributions for time-dependent finite-wing motions."

Report presenting the aerodynamic stability derivatives and pitch and yaw control effectiveness of two full-scale guided bombs over a range of Mach numbers in free-flight drop tests. Results regarding performance information, roll control operation, and aerodynamic characteristics are provided.

Report discussing testing on a research model to obtain experimental drag and heat-transfer data under constant and varying conditions of Reynolds number and heating effects. Average body turbulent skin-friction-drag coefficients were determined for both constant and varying heating effect.

Report presenting an investigation on a canard ramjet missile configuration to determine its lift and drag characteristics at low values of lift. Two rocket-boosted models that differed only in the size and deflection of the canard were used. Information about the trim lift characteristics, drag, and stability is provided.

The behavior of insoluble corrosion products in the HRT is generally understood and studies of the removal of these solids by hydroclones can logically be terminated after the effect of higher processing rates by the multiple hydroclone has been determined. Chemical descaling may be required to supplement solids removal by hydroclones. Laboratory studies to find suitable reagents will be continued in conjunction with decontamination work presently in progress.

Documentation outlining characteristics of field data samples taken in the Rapid City quadrangle.

This summary of the research progress meeting on June 17, 1948 discusses the following topics: (1) Potassium 43 (R. Overstreet); (2) Recoils (A. Ghiorso); (3) M.I.T. accelerator conference (W. Panofsky); and (4) Cosmic rays (Prof. Louis Le prince - Ringuet, France)

Report containing information regarding He4 vapor pressure measurement as of 1958, the recent history of the vapor pressure temperature scale, and a series of tables containing these measurements.

Abstract: Exposure of Sprague Dawley white rats to single doses of 900 kvp X radiation demonstrated a medium lethal dose of 600 r which was not markedly dependent upon sex, weight, or, in the case of females, stage of the estrous cycle at the time of irradiation. Deaths within 30 days were most frequent between the fourth and eighth, and between the tenth and fifteenth post- irradiation days, indicating the existence of at least two processes leading to death in the "acute" period.

Abstract. The rate constants for the reaction of the hydrated electron eaq with a number of solutes and with radicals formed in water radiolysis are reported. Hydrated electrons were formed in the electron pulse irradiated solutions at concentrations in the range from 1 to 10 pM. Their reaction was followed by the decay of the optical absorption of eaq at 5780 A. Generally a 04 psec pulse of 15 MeV electrons was used. In the absence of eaq scavengers, second-order kinetics prevailed owing to the dominance of the reactions,eaq+eaq, eaq+H, and eaq+H202 when OH radical scavengers were present in alkaline solution. An analysis of the decay curves leads to values for keaq+eaq and keaq+H of 0.9~ 1010 and 3 x 1010 M-1 sec-1, respectively. With scavenger present in excess over [eaq], pseudo first-order kinetics were found and rate constants for a number of inorganic and organic compounds are reported. The agreement of these and other rate constants with diffusion-controlled reaction theory is discussed.

Detailed study of the mathematically developed end-point method and its application to the Milne kernel.

Describes the current prototype model of a linear amplifier, two-channel pulse-height analyser, two-channel count-rate meter, and count-rate difference detector for a gamma-ray spectrometer monitor developed to approach the above design criteria.