Report that discusses the possibility of testing the T-invariance in μ-meson decay. The author describes a past experiment performed by Lee and Yang, as well as the specifics of the proposed experiment to test the time reversal in μ-meson decay.

Memorandum presenting an analysis to determine the feasibility of using a constant diffuser Mach number to position a translating spike for optimum inlet performance. A control system incorporating this concept was investigated on a blunt lip, translating-spike inlet at flight Mach numbers of 1.8 to 2.0 and angles of attack up to 6 degrees. Results regarding inlet characteristics and performance with control are provided.

"The equations are presented for the development of the compressible laminar boundary layer over a yawed infinite cylinder. For compressible flow with a pressure gradient the chordwise and spanwise flows are not independent. Using the Stewartson transformation and a linear viscosity-temperature relation yields a set of three simultaneous ordinary differential equations in a form yielding similar solutions. These equations are solved for stagnation-line flow for surface temperatures from zero to twice the free-stream stagnation temperature and for a wide range of yaw angle and free-stream Mach number" (p. 1017).

Report presenting an investigation of the transonic flutter characteristics of two 64 degree sweptback delta wings. Both of the wings had simulated streamwise ribs and orthogonal spanwise spars, but the wings had different stiffness and mass.

Report presenting an investigation by the transonic-bump method of the static longitudinal aerodynamic characteristics of a series of swept, highly tapered, thin wings in the high-speed 7- by 10-foot tunnel. Testing occurred over a range of Mach and Reynolds numbers and angles of attack. Results regarding lift and drag characteristics and longitudinal stability characteristics are provided.

Report presenting an investigation to determine the reductions in temperature-recovery factor associated with pulsating flows generated by spike-nose cylinders. The investigation was conducted at zero angle of incidence at a free stream Mach number of 3.50 and a free stream Reynolds number of 1.73 million.

Report presenting an investigation on an airplane model with drooped horizontal tail and a highly tapered wing of aspect ratio 2.8 and 45 degrees of sweep. The primary purpose of the investigation was to determine what improvements in the control of leading-edge stall would be possible with the use of area suction on a leading-edge flap and with the leading-edge flap used with a modified or bulbous leading edge and chord extension.

Report presenting a transonic flutter investigation of models of a wing of a new fighter airplane with an arrowhead plan form, ailerons at the tips and flaps, and was cantilever mounted. Results regarding the run, point, panel behavior, scaling, and a comparison of the basic, modified, and locked ailerons are provided.

From Introduction: "This report describes some measurements of these quantities obtained by crashing fighter aircraft under circumstances approximating those observed in service."

Report presenting an investigation of a free-flight test vehicle to obtain boundary-layer-transition and heat-transfer data. The model had a 15-degree-included-angle cone-cylinder and a 10 degree conically flared afterbody. Results regarding the free-stream conditions, conditions at outer edge of boundary layer, temperatures and heat-transfer coefficients, and boundary-layer stability conditions are provided.

Report presenting a turbojet-engine-exhaust simulator utilizing a hydrogen peroxide gas generator developed for powered-model testing in wind tunnels with air exchange. The problems associated with jet exhaust simulation in a transonic wind tunnel which led to the selection of a liquid monopropellant are discussed. Static-data obtained with convergent nozzles are presented and shown to be in good agreement with ideal calculated values.

Report presenting testing of a series of rocket-propelled general-research test missiles incorporating cruciform delta wings mounted along the diagonals of a fuselage of square cross section used to obtain longitudinal trim in flight. Several combinations of controls and static and dynamic longitudinal stability of the missiles were tested at a range of Mach numbers.

From Introduction: "The design and flight evaluation of an airborne target simulator for use in tracking studies of fighter-type airplanes equipped with optical gunsights have recently been reported (ref. 1). In this equipment the target airplane was represented by a movable dot of light projected on the windshield of the test airplane."

Memorandum presenting a survey of the present status of theory in the field of slip-flow aerodynamics, which leads to the conclusion that the Navier-Stokes equations of motion together with first-order velocity slip and temperature jump at any boundary are sufficient insofar as experimental confirmation is available.

Discussing holes drilled in order to evaluate the uranium potential of the Red Canyon area, in San Juan County, Utah.

The measured pressure drop across the reactor core, with the sample holder in place, is 6.9 psi, more than twice the estimated value. Better estimates, based on more rigorous mathematical analysis, should be possible for future problems of this type. The 2% density difference which produced the relatively high velocity of approximately 1 fps, in this experiment, will result from a temperature difference of about 8 C. It is concluded that the bulk fluid temperature near the sample holder will be less than 8 C above the average temperature at the same elevation in the core.

In order to evaluate the behavior of an APPR type absorber rod, an irradiation test program has been established. Approximately 21 more samples are planned for testing under this request. The request proposes testing a full size APPR-1 type control rod in the MTR. The objective of the test is to better evaluate the neutron absorbing material proposed for the APPR-1 control rod.

The operation and design of a high pressure recombination loop for the recombination of H2, D2, and O2 produced by the radiolytic decomposition of water which is used a solvent for fuel in the homogeneous reactors are presented.

An estimate has been obtained of the heat that should be generated in the HRT core in order to hold the system at operating temperature under no-load conditions. This estimate was made by measuring the feed-water rate to the package boiler during an oxygenated water rung. Results are summarized.

During the pre-startup phase of the HRT operations, moisture was accidentally introduced into the charcoal bed adsorbers in the off-gas system. Tests have been made to determine the effect of wetting upon the adsorptive properties of the charcoal. The work was divided into two phases, testing of fresh charcoal in the laboratory and testing of the HRT charcoal beds in situ. It is recommended that the beds be dried by heating them to about 40 C and purging each with one to two liters/min of dry instrument air.

The expected performance of the HRT carbon beds was calculated for various reactor operating conditions. the calculations indicated that the flow rate of sweep gas will have to be limited to prevent excessive activity discharge. Data on activity discharge are included.