A quarterly summary of reports that have been published on research being conducted at the University of California Radiation Laboratory

"Calculations have been made to find ranges attainable by bombers of gross weights from l40,000 to 300,000 pounds powered by turbine-propeller power plants. Only conventional configurations were considered and emphasis was placed upon using data for structural and aerodynamic characteristics which are typical of modern military airplanes. An effort was made to limit the various parameters invoked in the airplane configuration to practical values" (p. 1).

A method is described by means of which the laminar friction layer at a wall with arbitrary pressure distribution may be calculated from Prandtl's boundary-layer equations.

Report presenting additional wind-tunnel tests of a model of the X-3 airplane at low and high subsonic numbers to investigate the lateral and longitudinal-stability and control characteristics. Results regarding the aerodynamic characteristics in pitch and aerodynamic characteristics in yaw are provided.

Contents: Preliminary notes on the efficiency of propulsion systems; Part I: Propulsion systems with direct axial reaction rockets and rockets with thrust augmentation; Part II: Helicoidal reaction propulsion systems; Appendix I: Steady flow of viscous gases; Appendix II: On the theory of viscous fluids in nozzles; and Appendix III: On the thrusts augmenters, and particularly of gas augmenters.

This document presents equations for the two-dimensional stationary problem of gas dynamics, and uses them to derive other equations, including equations for vorticity.

Report presenting force testing on an NACA 3-(3)(05)-05 eight-blade dual-rotating propeller at a range of blade angles. Results indicated that good efficiencies can be obtained at high subsonic forward Mach numbers by operation at high blade angle. Results regarding the propeller characteristics, individual power coefficients, effect of forward Mach number on the maximum efficiency of the dual propeller, and effect of small changes in the rear-propeller blade angle on the dual-propeller characteristics are also provided.

An investigation was conducted to determine the effects of water injection on the over-all performance of a modified J33-A-27 turbojet-engine compressor at the design equivalent speed of 11,800 rpm. The water-air ratio by weight was 0.05. With water injection the peak pressure ratio increased 9.0 per- cent, the maximum efficiency decreased 15 percent (actual numerical difference 0.12), and. the maximum total weight flow increased 9.3 percent.