Memorandum presenting some effects of aileron deflection on the static lateral and directional aerodynamic characteristics of four airplane models which are representative of aircraft capable of flight at supersonic speeds. The results are presented for subsonic Mach numbers ranging from 0.60 to 0.90 and for supersonic Mach numbers ranging from 1.20 to 1.90. They are limited to the most pertinent aerodynamic effects of ailerons contributing to the lateral and directional characteristics of each airplane type.

Memorandum presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback in order to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Close to theoretical flap effectiveness was obtained with blowing flaps deflected 45, 55, and 65 degrees at low angles of attack. Results regarding the wind tunnel, take-off performance, landing performance, and comparisons with flight data are provided.

Report discussing an investigation into the binding of amorphous carbon with flourine to render it inert and easy to vent into the atmosphere.The ease and safety of the procedure are described.

Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.

Report presenting an experimental investigation to determine the effects of simulated engine nacelles on the flutter characteristics of a cambered A-plan-form wing with 45 degree sweepback of the leading edge, an aspect ratio of 3.6, and a taper ratio of 0.14. Results regarding a wing-mount fixed and a model with wing mount free are provided.

Memorandum presenting a low-velocity-turning stator designed to reduce secondary-flow loss cores by turning the flow at low velocities and accelerating it in passages of constant flow angle with reduced cross-channel pressure gradients. Performance of the stator was determined with static-pressure measurements and detailed surveys of total pressure and flow angle made with the turbine operating at design speed near design work.

Memorandum presenting a brief summary of the recent theoretical and experimental work on local heat-transfer rates on blunt-nose bodies. Results regarding the calculation of local flow conditions, prediction of stagnation-point heating rates, and calculation of heating rates over entire nose are provided.

Memorandum presenting a survey of the problems introduced by the increased longitudinal stability and reduced directional stability of aircraft operating in the low supersonic speed range. Information regarding longitudinal stability and directional stability are provided.

"Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory" (p. 1).

Report discussing the flutter characteristics of several control-surface configurations, including a wing with tip ailerons, an all-movable stabilizer, vertical tails with trailing-edge rudders, a t-tail, and some simple models of all-movable controls. Some trends of the configurations and suggestions for improving the flutter characteristics are provided.

Memorandum presenting a theory for evaluating the mutual interference between a wing and tip tank as extended to apply to store-pylon configurations. By using the theory and the flow-field formulas of a previous report, theoretical store-pylon side-force estimates have been made for a number of store-pylon configurations. Results regarding the theory for store-pylon side force, scope of test configurations, contribution of store and pylon to combined load, effect of store spanwise location on the store-pylon side-force coefficient, effect of pylon sweep and store chordwise location, effect of sideslip on the store-pylon side-force coefficient, effect of fins on store side-force coefficient, and interference effects between inboard and outboard stores are provided.

"The frequency content of the control input and resulting airplane motions is presented as power spectral densities for one operational flight of the fighter airplane (Republic F-84G). The frequency content, which is described by the shape of the spectrum, may be useful in providing inputs for the design of power control systems. For normal load factors, the results presented for the operational flight considered are in general agreement with the results of more complete data on three fighter airplanes (Republic F-84G, Republic F-84F, and North American F-86A)" (p. 1).

The flow fields near a 45 degree swept-wing-fuselage combination at moderate angles of sideslip (plus-or-minus 8 degrees), as determined experimentally at low speed, are presented as variations with chordwise distance for various spanwise and vertical locations and angles of attack. The results indicated that for positions close to the fuselage (on and near the plane of symmetry) changes in the angle of sideslip caused large changes in the flow-field characteristics and particularly in the local angles of sideslip, which in some cases were nearly double the static angle of sideslip.

Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in two representative after-burning positions. Jet-thrust and air-handling data were obtained in quiescent air for 4 selected ejector configurations over a wide range of secondary to primary airflow ratios and primary-nozzle pressure ratios. The experimental ejector data are presented in both graphical and tabulated form.

"The multistage turbine from the J73 turbojet engine has previously been investigated with standard and with reduced-chord rotor blading in order to determine the individual performance characteristics of each configuration over a range of over-all pressure ratio and speed. Because both turbine configurations exhibited peak efficiencies of over 90 percent, and because both units had relatively wide efficient operating ranges, it was considered of interest to determine the performance of the first stage of the turbine as a separate component. Accordingly, the standard-bladed multistage turbine was modified by removing the second-stage rotor disk and stator and altering the flow passage so that the first stage of the unit could be operated independently" (p. 1).

Report presenting an investigation conducted to determine the overall performance of the J73 two-stage turbine with a standard rotor-blade configuration. The turbine operated with a maximum brake internal efficiency between 0.91 and 0.92 at an overall pressure ratio of about 3.4 and 120 percent equivalent design rotor speed. Results regarding the overall performance, variation of equivalent weight flow with overall pressure ratio, and effect of limiting blade loading are provided.

Report presenting an investigation to determine the feasibility of utilizing a reduced-chord rotor blading on the two-stage turbine of the J73 turbojet engine in order to reduce the weight. The turbine was operated as a component over a range of speeds and overall pressure ratios at turbine-inlet conditions corresponding to 35 inches of mercury absolute and 700 degrees R. Results regarding the overall performance, performance map, and peak efficiency are provided.

Report presenting an investigation of a reduced-chord multistage turbine at design speed and various turbine-inlet pressures from 12 to 40 inches of mercury absolute. At each inlet pressure, the turbine was operated over a range of overall turbine total-pressure ratios; turbine-inlet temperature was maintained at 700 degrees R. The results indicated that no appreciable effect on turbine overall performance was observed over the range of turbine-inlet total pressures investigated.

Report presenting a study of the first stage performance characteristics of the two-stage turbine from the J73 turbojet engine. The reduced-chord first-stage turbine operated at a peak brake internal efficiency of over 91 percent at a stage overall pressure ratio of 1.4 and at 90 percent of the design equivalent speed. The unit exhibited high efficiency over a wide range of operating variables.

Report presenting an evaluation of the stage performance of the J73 turbine on the basis of previous performance investigations of the first stages alone and of the two-stage turbines with standard and with reduced-chord rotor blading for a range of rotational speeds and pressure ratios. The results demonstrated that both of the two-stage turbines and first-stage turbines had comparable performance.

"Forty-three cylinders of 40-inch length and 16-inch diameter, made of 5052-0 aluminum-alloy sheets of 0.023-, 0.040-, 0.051-, and 0.064-inch thickness, were subjected to bending moments constant along the cylinder and in time in an oven which maintained a constant temperature of 500 degrees Fahrenheit during the test. All the cylinders failed by buckling. The time that elapsed between load application and collapse was measured" (p. 1).

Report presenting an investigation of the problem of predicting the experimental wave drag for configurations which have discontinuities in area distribution and thus infinite theoretical wave drag. The agreement between the experimental and computed drags of the ring-body combinations without fillets was very poor. Results regarding the drag coefficients and estimation of wave drag and pressure coefficients and estimation of total drag are provided.

Memorandum presenting a procedure for reducing the interference pressure drag of the root and tips of sweptback wings. Experimental and theoretical pressure-drag values over a range of Mach numbers for configurations designed by the method were compared with the values of two similar configurations designed by the transonic and supersonic area-rule methods. Results regarding total drag, pressure drag, and drag comparison are provided.

Report presenting an investigation of the certain wing-body combinations as measured by the lift-drag ratio for two arrangements: a half-cone mounted under a triangular wing and a half Newtonian ogive similarly mounted. The configurations were tested for a range of Mach numbers from 1.5 to 5.0. Results regarding the comparison of a half-cone versus a full cone and calculated maximum lift-drag ratio are provided.