"At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord split flaps, deflected 60 degrees, in the center of the wing and having flat span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively" (p. 1).

From Summary: "Surveys of the air flow in the region of the tail surfaces of a single-engine pursuit-type airplane equipped with dual-rotating propellers are presented."

Report presenting force tests of the NACA 23012 and 23012-64 airfoils of 24-inch chord in the high-speed wind tunnel at a range of Mach numbers. The results show the variation with mach number of lift, drag, and pitching-moment coefficients at a range of angles of attack.

Report presenting a theoretical analysis of the performance of propellers extending to high values. Charts are presented that facilitate the selection of the most efficient propellers over a wide range of operating conditions.

Report presenting a series of boundary-layer surveys over the surface of an NACA 0012 airfoil at zero lift. Results regarding the pressure distribution, laminar boundary layer, transition, turbulent boundary layer, drag, and skin friction are provided.

Report presenting flight tests of the flying qualities of numerous airplanes made to provide a fund of quantitative data for correlation with pilots' opinions of controllability, stability, and handling characteristics. A program was instituted which covered the various phases of work required.

Report presenting the flying qualities of the Supermarine Spitfire airplane. A variety of information regarding the construction, installation, longitudinal stability and control, and lateral stability and control are provided.

From Introduction: "The present paper deals with control surfaces having plain-overhang and Frise balances."

Report presenting problems relating to the stability and control of tailless airplanes in consideration of contemporary experience and practice. Some observations in regards to small and large airplanes are provided.

Report presenting an investigation of the size and distribution of ice particles on the wings of aircraft and how they affect the aerodynamic characteristics. A simulated ice formation was generated from survey information received from aircraft pilots and was tested to determine the impact on the lift characteristics.

Report presenting information regarding the calculation of the transition point, velocity distribution in laminar and turbulent boundary layers, and thickness of the boundary layer, both laminar and turbulent, of low-drag wings.

Report presenting tests made in the variable-density wind tunnel of airfoils of the NACA 4400 series modified by reflex at the trailing edge designed to reduce the pitching moment to the value of -0.03. The modified airfoils are designated the NACA 4400R series.

Report presenting an analysis to determine the effect on propeller performance of extension flaps added to the trailing edge of a propeller blade. A method is included to determine the angle that the flap extension must make with the chord in order to obtain a particular load distribution.

Report presenting the deceleration of air from supersonic velocities in channels. A normal shock in the diverging part of the diffuser is probably necessary for stable flow, and ways of minimizing the intensity of this shock have been developed.

Report presenting testing of preformed copper fins which were furnace-brazed to a steel-cylinder barrel. The barrel was electrically heated and blower-cooled to determine heat overall heat-transfer coefficient. Information regarding potential future adaptations of the fins are provided.

Report presenting a theoretical study of a diesel engine-compressor-turbine combination for aircraft application. The performance characteristics of the compressor and turbine chosen for analysis are believed to be attainable on present aircraft equipment.

Report presenting an investigation of the stalling characteristics of the Supermarine Spitfire, which was made as part of the flying-qualities measurement of the airplane. The results are presented in the form of time histories of the motions and controls during stalls in various conditions of flight. Generally, the Spitfire possessed good stall warning in the form of buffeting and stall motions were not violent.

Report presenting a consideration of the general problem of stalling as affecting the safety of airplanes. The increased difficulties associated with modern efficient wings, particularly highly tapered wings and high-life devices, are discussed and means are considered for avoiding these difficulties.

Report presenting tests performed in German and Italian supersonic tunnels to determine the aerodynamic characteristics of projectiles of various shapes. The results show that increasing the relative length of the nose causes the drag coefficient to decrease and the center of pressure to move forward.

Report presenting an investigation of the flow downstream from a two-dimensional grid formed of parallel rods. The nature of the flow was determined primarily by means of total-head measurements. Preliminary tests were made in both the closed-duct and open, two-dimensional configurations, but it was found that the same phenomenon occurred in both cases.

From General Analysis: "The purpose of part I of this paper is to show how the loading that gives the minimum induced energy loss can be obtained from rather elementary considerations and to present design charts from which such a plan form can be quickly obtained for any set of design conditions."

Report presenting values of the circulation function for dual-rotating propellers. Numerical values are given for four-, eight-, and twelve-blade dual-rotating propellers and for advance ratios from 2 to about 6.

Report presenting charts relating helicopter aerodynamic design variables to performance in steady powered flight. The flight conditions covered are hovering, climb, and horizontal flight. The use of the charts is illustrated by numerical examples in order that computations can be made for particular problems.

From Introduction: "Flight tests with electricity heated propeller-blade shoes reported in references 1 and 2 have establish the practicability of protecting propeller blades from ice formations by thermal-electric means."