The following report presents a discussion of the method for hydrodynamic problems, together with some new considerations that have arisen concerning the method.

"This report is written as a supplement to LAMS 2539. It is hoped that one will be able to read LAMS 2539, with emphasis on the fourth part (Memorandum N-4-79OU by 0. Farmer), with this memorandum to bridge the gaps and understand more about the model used and what the KIB Program can be used for. The system is defined by subsystems or subprograms: Thrust System, Heat Exchanger, Neutron Dynamics, Rod Actuator Dynamics, and Thermocouple Dynamics. The original Kiwi-B Flow System is included in the first part of LAMS 2539. This has been replaced by the newer system which includes a turbo-pump (per R, Bohl & E. Wheatley). This system will not be included here. Recommendations are made for improvement and more work in certain areas."

Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.

Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.

Report presenting an investigation of ram-jet-engine control by shock positioning on a 16-inch fixed-geometry ram jet at a range of free-stream Mach numbers. The control method appears to offer adequate control of ram-jet-engine operation. Results regarding the steady-state performance, effect of control settings on response and stability, effect of disturbance size and Mach number on response to fuel-flow disturbances, Mach number disturbances, angle-of-attack disturbances, exhaust-area disturbances, and recovery from subcritical engine operation are provided.

Report presenting measurements in free fall at transonic speeds of the dynamic stability characteristics of three models. Two of the models had 45 degree swept wings of aspect ratio 6 and 45 degree swept tail surfaces and differed only in that one had plane wings and one was cambered and twisted. The third had the same fuselage-tail arrangement but no wing.

Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick rounded nose sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.

Report presenting buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings for a jet-powered bomber airplane equipped with reflexed flaps and ailerons and tail-tip-incidence changes.

Report presenting testing of the rolling effectiveness and drag of half-delta wing-tip ailerons on rectangular and tapered wings sweptback 0 and 45 degrees for a range of Mach numbers. The rolling effectiveness was relatively uniform across the Mach number range and was lower at subsonic speeds and higher at supersonic speeds than the partial-span plain ailerons.

From Summary: "Experimental performance of a rocket engine using 15 percent fluorine-85 percent oxygen and JP-4 was compared with that obtained using oxygen and JP-4. The regeneratively cooled engine was operated at 5000 pounds thrust and a chamber pressure of 350 pounds per square inch absolute. The peak specific impulse from 15 percent fluorine was 251 pound-seconds per pound. This is an increase of 3.3 percent over the 243 pound-seconds per pound obtained with fluorine."

"A rapid design method based on stream-filament techniques was developed to obtain the boundaries of an annular combustor-inlet diffusr from a given stagnation streamline, given boundaries of the combustor liner, and given inlet and terminal velocities" (p. 1).

"A free-jet investigation of the performance of the XRJ43-MA-3 ram-jet engine has been conducted in an altitude test chamber at the NACA Lewis Laboratory. It is the purpose of this report to compare the performance and rich blow-out limits of the various engine configurations and diffuser orientations with the basic or standard engine configuration" (p. 1).

Abstract: The experimentally determined exponential dependence of spontaneous fission rate on Z^2/A has been used to derive an expression for the dependence of the fission activation energy on Z^2/A. This expression has been used to calculate the activation energy for slow neutron induced fission and photofission. The correlation with the experimental data on these types of fission seems to be quite good.

Report summarizing the progress of the gasket development program during the period from November 1949 to May 1950.

From summary: "In previous project work, dilute mixtures of inorganic cations in aqueous solution have been concentrated by adsorption of the cations on a synthetic resin and they have been fractionated by selective desorption of the cations from the resin. In this report..the general procedure used in chemical separation, the equipment used, and the theory of the exchange equilibria and of the reaction rates are presented."

Report containing a survey of the radiation from the nuclear ship Savannah in order to determine the dose rate for people aboard.

"The results of an experimental investigation made for the purpose of developing suitable jet-engine nacelle designs for a high-speed medium bomber are presented. Two types of nacelles were investigated, the first enclosing two 4000-pounds-thrust jet engines and a 65-inch-diameter landing wheel and the second enclosing a single 4000-pounds-thrust jet engine. Both types of nacelles were tested in positions underslung beneath the wing and centrally located on the wing" (p. 1).

"A General Electric fuel and torque regulator was tested in conjunction with a T31-3 turbine-propeller engine in the sea-level static test stand at the NACA Lewis laboratory. The engine and control were operated over the entire speed range: 11,000 rpm, nominal flight idle, to 13,000 rpm, full power. Steady-state and transient data were recorded and are presented with a description of the four control loops being used in the system" (p. 1).

This report was written from the notes used by Dr. York in delivering his three lectures on considerations pertinent to the problem of utilizing controlled thermonuclear reactions for the production of power. The first lecture discussed fundamental properties of the DD and DT reactions and the reacting substances. The second lecture described the stellarator, a proposed machine for the controlled production of power from the above reactions. The third lecture described the pinch effect and considered its possible application to the thermonuclear power problem.