"Theoretically derived charts and equations are presented by which tail-rotor design studies of directional trim and control response at low forward speed can be conveniently made. The charts can also be used to obtain the main-rotor stability derivatives of thrust with respect to collective pitch and angle of attack at low forward speeds. The use of the charts and equations for tail-rotor design studies is illustrated. Comparisons between theoretical and experimental results are presented. The charts indicate, and flight tests confirm, that the region of vortex roughness which is familiar for the main rotor is also encountered by the tail rotor and that prolonged operation at the corresponding flight conditions would be difficult" (p. 1).

Note presenting an investigation of the phenomena encountered when a plane oblique shock wave is incident upon the boundary layer of a flat plate. The flow field was divided into a viscous layer near the wall and a supersonic potential outer flow. With the outer flow determined, boundary-layer growth and pressure distribution were computed and results for the laminar cases were obtained and provided.

Report presenting an investigation on a body of revolution with a sweptback wing with a 0.25-mean-aerodynamic-chord point at the maximum body diameter and 1.2 mean aerodynamic chords behind the maximum diameter. The fuselage had a fineness ratio of 10, a 45 degree swept wing with an aspect ratio of 4.0, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Lift, drag, pitching moments, and angles of attack were measured at a range of Mach numbers.

Report presenting an investigation of the hypersonic similarity law for steady flow about bodies of revolution by correlating the forces and moments from tests at a range of Mach numbers and angles of attack. The data for the lifting cones and ogives are correlated by the hypersonic similarity law. Results regarding the similitude for lift and pitching moment and similitude for drag are provided.

Report presenting the results of strength tests on thick-skin wing structures. Some of the factors that were found to have influence on the buckling behavior and strength are shown with data and the conditions under which a combination of multiweb and multipost construction may be used are discussed. Results regarding circular-arc airfoils, multiweb beams, and multipost stiffened beams are provided.

Report presenting a flight investigation of the aerodynamic loads of a partial-span extended leading-edge slat on the 35-degree sweptback wing of the Douglas D-558-II research airplane. The slat normal-force coefficient was found to increase with airplane normal-force coefficient until peak slat normal-force-coefficient was reached at approximately 2.2 to 2.4.

Memorandum presenting a screening of various hydroxides for use in nuclear reactors as possible coolant moderators for operation at temperatures of about 1500 degrees Fahrenheit. The hydroxides that appear stable at a pressure of about 1 atmosphere are those of sodium, potassium, rubidium, lithium, barium, and strontium. Results regarding the core uranium investments and reflector savings are provided.

Report presenting the development and use of a chart for use in estimating the combustion efficiency of a turbojet at altitude flight conditions. The combustion efficiency chart is based on the assumption that the corrected gas flows, pressures, and temperatures of engine components other than the combustor are unique functions of corrected engine speed.

From Summary: "Flat, plate-type elements, 3.5 by 0.5 by 0.070 inches in size and containing 10 percent elemental natural uranium, were produced by hot pressing. The elements were acid-treated to remove surface uranium and then coated with an alumina glaze. Such an element remained stable and did not lose detectable quantities of fission fragments in a 400-hour treatment at 1800 degrees F in a flux of 5 X 10 to the 11th power neutrons per square centimeter per second. Such elements are conveniently produced and, dependent on design and on the successful resolution of problems such as thermal shock, offer a possible method of increasing air-cycle element temperatures and related performance."

Report presenting static-longitudinal stability and trim results using the XF-92A delta-wing research airplane during power-plant demonstration and US Air Force performance tests for Mach numbers up to 0.97 and altitudes from 11,000 to 40,000 feet.

Report presenting methods for estimating the aeroelastic effects and structural requirements of rocket-propelled model-booster combinations that are nearly symmetrical. The methods differ principally in the manner in which booster stiffness, reference axis, and inertia loading are considered. Special conditions and accuracy for each of the three models are provided.