Report presenting the aerodynamic characteristics of the NACA 0012 airfoil section at a range of angles of attack from 0 to 180 degrees. Data were obtained at two different Reynolds numbers depending on whether the airfoil surfaces were smooth or had roughness applied at the leading and trailing edges. After the stall with the rounded edge of the airfoil foremost, a second lift-coefficient peak was obtained at an angle of attack of about 45 degrees.

From Introduction: "Beyond the position where the boundary layer treatment can no longer be used, curves have been faired to connect the Nusselt number results of the present analysis with those of reference 3, in which a parabolic velocity profile is assumed throughout the entire duct length. So that a comparison could be made with the results of reference 3, the boundary layer analysis was used to study the development of the temperature profile associated with a parabolic velocity profile throughout."

Note presenting theoretically derived charts showing the profile-drag-thrust ratio for a helicopter rotor operating in forward flight and with hinged rectangular blades with a linear twist of -8 degrees. The charts, which show the profile-drag characteristics of the rotor for various combinations of pitch angle, ratio of thrust coefficient to solidity, and a parameter representing shaft power input, are presented for tip-speed ratios ranging from 0.05 to 0.50.

Report presenting flight testing and a mathematical analysis to demonstrate and confirm a type of subsonic flutter involving rigid-body motions and wing deformations. The period of oscillation was approximately 100 chords per cycle, which is well within the range of period found in dynamic-stability work on rigid aircraft with free controls. Results regarding the Rayleigh-Ritz treatment in four degrees of freedom, effect of various binary and ternary combinations of freedoms, and effect of relative positions of wing and missile center of gravity are provided.

Report presenting tests of two models for which the rate of change of sidewash with angle of sideslip could be varied. Both models were tested in steady-yawing flow and by the freely damped oscillation-in-yaw technique to establish the effect of the lag of the sidewash on the unsteady lateral damping of the models. Results regarding the model with auxiliary fins and model with wings in various vertical positions are provided.

Report presenting fluid-dynamics studies of simplified model fuel tanks mounted on a mechanism that simulated a wing undergoing torsional oscillations. The tanks were mounted in several configurations and the effective moment of inertia of the fluid was determined experimentally. Results regarding the effect of frequency, pylon-mounted tanks, centrally mounted tanks, and effect of a diffused baffle on the damping factor are provided.

Report presenting an investigation of the effects of many of the parameters significant to wing flutter on several untwisted rotating models to determine their significance with respect to stall flutter of propeller blades. The parameters included torsional stiffness, section thickness ratio, sweepback, length-chord ratio, section center-of-gravity location, blade taper, Mach number, and fluid density. Results regarding the considerations on method of presentation, experimental data and discussion, some possible applications, and a comparison of experiment with classical-flutter theory are provided.

Report presenting an experimental evaluation of the mean and turbulent momentum terms in fully developed turbulent pipe flow. The terms of the longitudinal-direction momentum equation, obtained from the Reynolds equations of turbulent fluid motion, were experimentally evaluated in a 4-inch-diameter pipe from total- and static-pressure data and hot-wire anemometer surveys.

"Measurements were made of the resistance of fibrous-glass compacts to normal air flow. The flow resistance was related to the thickness and density. As a porous material for boundary-layer-control applications using area suction, the fibrous-glass compact could be made to any desired thickness and permeability and sandwiched between perforated rigid surfaces" (p. 1).

"Measurements were made of the resistance of fibrous-glass compacts to normal air flow. The flow resistance was related to the thickness and density. As a porous material for boundary-layer-control applications using area suction, the fibrous-glass compact could be made to any desired thickness and permeability and sandwiched between perforated rigid surfaces" (p. 1).

Report presenting an analysis of approximately 100,000 hours of V-G data from one type of four-engine civil transport airplane to determine the magnitude and frequency of occurrence of the gust loads and gusts. The data were obtained during routine operations over the course of seven years on five different routes. Results regarding the accelerations experienced, gusts encountered, operating airspeeds, gust-load envelopes, and gust-velocity envelopes are provided.

Report presenting an investigation of the effectiveness of a wing equipped with large-chord slotted flaps in rotating the thrust vector of propellers through the angles required for vertical take-off and for flight at very low speeds in the 300 mph 7- by 10-foot tunnel. Results regarding static-thrust condition, tests with forward speed, and comparison of results for plain-flap and slotted-flap configurations are provided.

Report presenting lubrication studies of bearings lubricated with liquids and solids in a bearing test rig under conditions of minimum lubricant flow. Six liquid lubricants were investigated, including two petroleums and four synthetics. Results regarding bearings with silver-plated beryllium copper cages, bearings with cast Inconel cages, and an analysis of experimental results are provided.

Note presenting linearized equations of motions which are derived for both conventional aircraft having mirror symmetry and spinning projectiles or missiles with rotational and mirror symmetry. The equations for aircraft are compared with those for missiles and shortcomings in the currently accepted theories are pointed out. The dynamic-stability requirements for spin-stabilized projectiles are discussed briefly.

Report presenting a low-speed investigation in the two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. Two models were tested: a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees and an inlet model with a triangular-shaped inlet installed in the wing root. Results regarding the original and modified inlets and the final inlet are provided.

Report presenting a series of curves that have been prepared to simplifying and accelerate calculation procedures for component or overall cycle performance of gas-turbine engines. The curves are based on the thermodynamic properties of air and combustion gases for a hydrogen-combustion ratio of 0.167.

Note presenting a method for studying the transient behavior of the flapping motion, as well as for calculating the steady-state flapping amplitudes, of free-to-cone and seesaw rotors operating at extreme flight conditions. The method is general and can be applied to blades of any airfoil section, mass distribution, twist, plan-form taper, root cutout, and flapping-hinge geometry.

Note presenting some methods of estimating the induced drag of low-aspect-ratio wings, which are discussed and compared with experiments. The profile drag due to lift is also discussed and a method is developed which relates the effect of aspect ratio on the profile drag due to lift to an "effective" two-dimensional lift coefficient.

Note presenting the assumptions of the Prandtl-Busemann small-disturbance method, together with the requirements of continuity and irrotationality, which lead to a recursive system of first-order partial-differential equations. The results of the analysis are applied to the case of subsonic flow past a parabolic cylinder.

Report presenting a rapid method for estimating the downwash behind swept-wing airplanes. The agreement with available experimental data taken behind airplane models is good. Results regarding the comparison with experiment and a comparison of the downwash due to a flat sheet and that due to a rolling-up vortex sheet are provided.

Report presenting a method of computing the losses in total pressure caused by a non-zero angle of attack at the inlet to a row of sharp-nosed blades for both incompressible and subsonic compressible flow. The method is based on momentum considerations across a row of zero-thickness flat plates and assumes that the blade force is normal to the plate surface.

Report presenting a theoretical method for calculating the flow field about a wing-body combination employing bodies deviating only slightly in shape from a circular cylinder. The method is applied to the calculation of the pressure field acting between a circular cylindrical body and a rectangular wing.

"The aerodynamic characteristics of indicially cambered two-dimensional airfoils in supersonic flow are determined theoretically. These indicial functions are used to determine the power required to sustain a general time-varying chordwise deformation. The harmonically oscillating parabolic mode is considered in detail and stability boundaries are presented for this case" (p. 1).

Report presenting an investigation to determine the effects of several factors associated with the propeller installation on the ability of a wing with plain flaps to deflect a propeller slipstream downward as a means for achieving vertical take-off. Some of the factors considered were propeller blade angle, mode of propeller rotation, propeller location, and ratio of wing chord to propeller diameter.