Suggested formula are given for determining air-cooled turbine-performance characteristics, such as power and efficiency, as functions of certain parameters. These functions, generally being unknown, are determined from experimental data obtained from specific investigations. Special plotting methods for isolating the effect of each parameter are outlined.

Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.

The effects of turbine-blade cooling on engine performance were analytically investigated for a turbojet engine in which cooling air is bled from the engine compressor. The analysis was made for a constant turbine-inlet temperature and a range of altitudes to determine the minimum cooling requirements to permit substitution of nonstrategic materials in turbine blading. The results indicate that, for a constant inlet temperature, air cooling of the turbine blades increases the specific fuel consumption and decreases the thrust of the engine. The highest possible cooling effectiveness is desirable to minimize coolant weight flow and its effects on engine performance.

Report presenting an investigation to determine the benefits obtainable by applying boundary-layer control to a 45 degree swept-forward wing-fuselage combination. Force and pressure-distribution data were obtained with and without boundary-layer control with various combinations of leading-edge and trailing-edge flaps.

Report presenting the aerodynamic characteristics of an all-movable, triangular-plan-form wing alone and with a body as determined from semispan model tests. The agreement between calculated and experimental results was not satisfactory for the most part, which seemed to be due to the failure of linear theory to define the actual flow field about the configurations investigated. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

A heat-transfer investigation was conducted with air in an electrically heated platinum tube with long-approach entrance, inside diameter of 0.525 inch, and effective heat-transfer length of 24 inches over ranges of Reynolds number up to 320,000, average inside-tube-wall temperature up to 3053 degrees R, and inlet-air temperature up to 1165 degrees R. Correlation of data by the conventional Nusselt relation resulted in separation of data with tube-wall temperature. Good correlation was obtained, however, by use of a modified Reynolds number.

Report discussing an investigation of the rolling effectiveness at transonic and supersonic speeds on a 38.1 degree sweptback tapered wing with NACA 0010-64 airfoil sections and partial-span ailerons of true contour with a modified flt-side blunt trailing-edge shape. The variation of Reynolds number with Mach number and the control effectiveness is provided.

Memorandum presenting the results of a free-jet investigation to determine the internal performance of a 16-inch ram jet. Data were obtained at a range of altitudes and Mach numbers. Results regarding the rake flame holder, effect of fuel injector on burner performance, effect of propylene oxide on burner performance, serrated annular baffle flame holder, diffuser performance, and performance at off-design spike location are provided.

From Introduction: "An investigation of the high-speed aerodynamic characteristics of a modified delta wing in combination with a fuselage was conducted in the Langley high-speed 7- by 10-foot tunnel. The model was tested on the sting support system through a Mach number range of 0.40 to 0.90 with both free and fixed transition. Because of the nature of the transition effect, the results seemed to be of the general interest and are presented in the present paper."

"An investigation of a 1/24-scale dynamically similar model of the Boeing B-47 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves" (p. 1).