From Introduction: "The results of analyses of V-G data given in references 1 to 5 have shown that the flight loads of airplanes operated in commercial transport service are influenced by operating speeds and by forecasting and dispatching practices as reflected in differences between operations during the prewar and wartime periods. The available data are summarized and the flight results are compared with the results of analyses made in references 1 to 5."

Report presenting procedures for solving the equations of equilibrium of reinforced panels and isolated fuselage rings as represented by the external loads and operations table established according to Southwell's method. By using these equations, the stress distribution can be easily determined.

Report presenting a new apparatus for varying the effective dihedral in flight by means of servo actuation of the ailerons in response to sideslip angle. Results regarding the characteristics of the effective-dihedral control in steady sideslips, in abrupt rudder kicks, and in lateral oscillations are provided.

Note presenting a procedure based on the Weissinger method so that the basic span loading and associated aerodynamic characteristics can be rapidly predicted for wings having arbitrary values of sweep, aspect ratio, taper ratio, and twist. A method for correcting for the effects of compressibility is given. Results regarding the evaluation of the method, effect of plan-form variation on the basic loading characteristics, and a consideration of twist in swept-wing design are provided.

Report presenting a low-speed wind-tunnel investigation of a scale model of an airplane with a 38.7 degree sweptback wing with an aspect ratio of 4.51, a taper ratio of 0.54, and conventional tail surfaces. Results regarding the lift characteristics, longitudinal stability, longitudinal control, directional stability, lateral control, and directional control are provided.

From Summary: "The problem of the loss in rolling effectiveness at supersonic flight speeds is considered for the case of the rectangular wing. Equations are obtained from which can be calculated either the loss in rate of roll due to flexibility or the torsional stiffness required to maintain a given rate of roll, for two assumed variations of the spanwise distribution of torsional stiffness. A computation form and figures are provided so that calculations can be made without reference to the details of the analysis."

"Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to have lift characteristics at supercritical Mach numbers which are favorable in the sense that the abrupt loss of lift, characteristic of the usual airfoil section at Mach numbers above the critical, is avoided. Aerodynamic characteristics determined, from two-dimensional windtunnel tests at Mach numbers up to approximately 0.9 are presented for each of the derived airfoils. Comparisons are made between the characteristics of these airfoils and the corresponding characteristics of representative NPiCA 6-series airfoils" (p. 1).

The results of an investigation to determine the two-dimensional lift and drag characteristics of nine NACA 6-series airfoil sections at three different Reynolds numbers and a comparison with a different report. The airfoils selected represent sections with variations in thickness, thickness form, and camber.

Note presenting calculations based on test data taken on a single-cylinder compression-ignition engine with a compression ratio of 13.1 and an engine speed of 2200 rpm to determine the performance at sea-level conditions of a compression-ignition engine geared together with a compressor and a turbine. The net specific power output increased with decreasing compression ratio and with increasing fuel-air ratio and engine speed.

Report presenting an analysis of a turbine-propeller engine operating at constant speed in order to provide information regarding factors influencing optimum proportionment of power between propeller and jet, improvement in engine performance attainable from controlled proportionment of power, and control relations for optimum proportionment of power.

Note presenting results of a flight investigation of a Curtiss XP-42 airplane equipped with an all-movable horizontal tail with a control system incorporating a combination of geared unbalancing tabs and servotabs. In order to increase the stick forces for rapid deflections without affecting the forces in gradual maneuvers, the servotab linkage was modified by incorporating a viscous damper in one of the links. An investigation of the arrangement showed that the control characteristics were generally satisfactory in rapid maneuvers as well as in steady flight.

Note presenting the results of an investigation conducted to determine the effect of tail length on the spin and recovery characteristics of a model typical of a trainer-type airplane. The model used in the investigation was tested with two tail lengths, and the model with the shorter tail was tested with several ventral fins. Results indicated that the model with the longer tail length had the better recovery characteristics even when the short tail model had comparable or higher levels of tail-damping power factor.

Report presenting an investigation of a powered model of a single-propeller low-wing airplane with three values of tail length and three horizontal tails to determine the effects of tail length and tail volume on the longitudinal and lateral stability.

Note presenting a high-speed wind tunnel investigation of a tapered wing of NACA 66-series airfoil sections equipped with split flaps conducted at Mach numbers up to 0.585 to determine the effects of compressibility on the normal-force, pressure, and load characteristics. Results regarding normal-force characteristics, span-load distribution, pitching-moment characteristics, and flap normal-force and hinge-moment coefficients are provided.

Report presenting an investigation in the impact basin to determine the hydrodynamic impact loads in rough water for a prismatic-float forebody with an angle of dead rise of 30 degrees. Testing occurred at fixed trim and each impact occurred into a 2-foot-high wave at 60, 45, or 30 feet in length. Results regarding the calculation of rough-water loads and comparison with smooth-water conditions are provided.

Report presenting the effects of antispin fillets and dorsal fins on the spin and recovery characteristics of airplanes as determined from an analysis of the results of spinning investigations of a large number of models tested in the 15-foot by 20-foot free-spinning tunnels. When antispin fillets were installed on an airplane, the fuselage area below the fillets became more effective in damping the spinning rotation. Results regarding the wake line, shielding of the fillets by the fuselage, and recovery characteristics are provided.

Report presenting analytical expressions derived from the downwash throughout the entire induced flow field of lifting triangles of infinite chord with the leading edges forward or behind the Mach cone. Results regarding the downwash charts, variation of downwash distribution with leading-edge sweep angle, and additional factors affecting the downwash are provided.