Note presenting an approximate method developed to predict the location of detached shock waves ahead of two-dimensional and axially symmetric bodies. The method is based on the continuity relation, which is applied to the air that passes the sonic line.

Note presenting a low-turbulence wind tunnel investigation of an NACA 64A010 airfoil with a porous surface of sintered bronze to determine the reduction in section drag coefficient that might be obtained at large Reynolds numbers by use of suction to produce continuous inflow through the surface of the model. Results regarding the uncompartmented model, compartmented model, observations on stability of laminar boundary layer, and theoretical calculations are provided.

Note presenting experimental pressure-time measurements along with schileren photographs of the unsteady-flow phenomena initiated in constant-cross-sectional-area passages. The methods of calculation of the flow phenomena are based on the assumptions of one-dimensional, nonviscous, unsteady flow.

Report presenting a comparison of the thermal performance and pressure-drop characteristics of heat exchangers on a heat-exchanger test stand. The exchangers included parallel and cross-flow units as well as extended-surface and all-prime-surface units.

Report presenting an investigation of seven hot-pressed ceramics for possible gas-turbine application. The properties, short-time tensile strength, thermal-shock resistance, coefficient of liner expansion, and density were determined. The ceramics tested were magnesium oxide, titanium carbide, zirconium carbide, boron carbide, silicon carbide with boron carbide, zircon, and zirconia with lime.

"A theoretical solution is obtained for the problem of the shear buckling of infinitely long simply supported elastic Metalite type sandwich plates. An approximate correction is suggested for the determination of the critical shear stresses of plates that buckle in the plastic range" (p. 1).

Note presenting thermodynamic properties of the products of combustion of five different mixtures of air with typical aircraft-engine fuel, which have been calculated from the most reliable thermodynamic data available. The calculations are presented in five charts of internal energy plotted against entropy with values of temperature, specific volume, pressure, and enthalpy indicated corresponding to five different percentages of the fuel-air ratio for perfect combustion.

Report presenting testing of five NACA airfoil sections intended for use in rotor blades in the two-dimensional low-turbulence tunnel. The airfoils varied in thickness and theoretical design lit coefficients. Results regarding pitching moment, lift, drag, and helicopter performance calculations are provided.