Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.

Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.

Report presenting testing to determine the interference effects of various sting-support configurations on the base pressure and foredrag characteristics of a wing-fuselage combination with a turbulent boundary layer. The primary variable investigated was the length of the constant-diameter portion of a sting support. Results regarding the base-pressure interference and foredrag interference are provided.

Memorandum presenting an investigation to determine the feasibility of increasing the specific weight flow of a transonic axial-flow compressor inlet stage by decreasing the hub-tip ratio. The current phase of the investigation was conducted to determine the blade-element and the overall performance of the complete stage. Results regarding the overall performance, blade-element performance, and stator-blade-element performance are provided.

Memorandum presenting an investigation of the performances of two annular diffuser designs applicable to turbojet afterburner installations to determine the effectiveness of injection and suction boundary-layer controls. Results regarding inlet measurements, flow observations, static-pressure distributions, downstream velocity distributions, and mean performance coefficients are provided.

Report presenting a flight program using the Northrop X-4 semitailless airplane to investigate the effect on the longitudinal and lateral stability and control of thickened elevons with trailing-edge thickness one-half the control-hinge-station thickness. The investigation consisted of speed runs, wind-up turns, abrupt rudder-fixed rolls, and longitudinal pulses between a range of Mach numbers.

Report presenting an investigation at the Lewis laboratory to develop air-cooled, strut-supported turbine blades. Six blades were investigated in a full-scale turbojet engine to obtain data on blade durability and blade-cooling effectiveness and strut temperature. Results regarding the heat-transfer investigation and blade-durability investigation are provided.

Report presenting the steady-state performance of the YJ73-GE-3 turbojet engine in an altitude test chamber for a range of exhaust-nozzle areas, simulated altitudes, and Mach numbers. A method of performance calculation based on engine pumping characteristics is provided. Results regarding performance maps, pumping characteristics and performance prediction, thrust correlation, effect of inlet temperature on performance, calculated performance from pumping characteristics, and altitude-ignition characteristics are provided.

"Small-perturbation spectral-analysis techniques are used to obtain the root-mean-square flame-generated turbulence velocities and the attenuating pressure fluctuations stemming from interaction of a constant-pressure flame front with a field of isotropic turbulence in the absence of turbulence decay processes. The anisotropic flame-generated turbulence velocities are found to be of about the same intensity as those of the incident isotropic turbulence, the lateral turbulence velocities being always lower, but the longitudinal velocity is somewhat increased for flame-temperature ratios over 7" (p. 599).

Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limitations.

Memorandum presenting the effectiveness of a body flare as a pitch-stabilizing device and a body flap as a pitch-control device investigated experimentally at Mach numbers from 3.00 to 6.25. The basic test body was rotationally symmetric and consisted of a fineness ratio 3 nose followed by a fineness ratio 9 afterbody. Results regarding the stability of the flared body, effect of body flap on lift and drag, trim conditions, flow visualization studies, and comparison of theory and experiment are provided.

A cermet composition was investigated as a potential material for gas-turbine blades. Blades of HS-21 alloy were also operated in the engine simultaneously to provide a basis of comparison. The cermet blades survived as long as approximately 312-1/2 hours at about 1500 degrees F with an average midspan centrifugal stress of approximately 11,500 psi.

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.

"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 a simple method for determining the nonlinear gains required to give optimum responses for step inputs of all magnitudes. The method is based on the fact that the control surface moves at its maximum rate during almost the entire transient maneuver and thus the servo system can be considered as a simple on-off type controller.

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.

"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).

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 the evaluation and analysis of the mean and turbulent terms of the equations of motion and the stress tensor at four stations in a turbulent boundary layer with a progressively increasing adverse pressure gradient. Report presenting mean flow parameters, summary of velocity measurements, evaluation of wall shearing stress, shear stress distribution across boundary layer, and stress tensor 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.

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 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 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.