Report discussing an investigation into the performance of several modifications of a side-inlet ramjet engine diffuser. Total-pressure-recovery profiles, Mach number profiles, longitudinal wall static pressure distributions, and variation of the average-static to average-total pressure are presented.

Report presenting experiments conducted on conical convergent-divergent nozzles having included a range of divergence angles and expansion ratios over a wide range of nozzle pressure ratios with cold flow to determine the effect of divergence angle on the internal performance of the nozzles. Results regarding the performance characteristics, effect of divergence angle on overexpanded performance, and effect of divergence angle on nozzle air-flow characteristics are provided.

Report presenting an investigation to determine the pressure drag of various blunt-based conical afterbodies at a range of Mach numbers. A generalized series of bodies was included which incorporated convergent nozzles discharging unheated jets at various pressures from the base. Results regarding the afterbodies without the jet and afterbodies with the jet are provided.

Report presenting an investigation of a shock-positioning control on a 16-inch ramjet engine at a range of Mach numbers and angles of attack in the supersonic wind tunnel. The control operated at all conditions under which the engine could be manually operated. Prediction of the control-system dynamic behavior can be applied by treating the system as having pure dead time.

Report presenting an investigation of a shock-positioning control on a 16-inch ramjet engine at a range of Mach numbers and angles of attack in a supersonic wind tunnel. The static-pressure rise across the inlet normal shock was utilized in setting the diffuser at its critical condition. Results regarding the sensing pressures, engine performance, control set engine operation, pressure data, operation of the control during Mach number change, and other applications of control are provided.

Report presenting an investigation of the screeching characteristics of two flame-holder configurations in a full-scale transpiration-cooled afterburner. The investigation indicated that a porous wall of wire cloth may be effective in eliminating or reducing the tendency to screech in some high-performance afterburners, but further testing is required. Results regarding the diametrical V-gutter, single-ring V-gutter, and durability of wire cloth are provided.

Report presenting a new blade series designed to operate at near choking inlet Mach numbers and to have near maximum critical Mach numbers by employing high aerodynamic loading of the profiles in the leading-edge region and relatively straight trailing edges. Results regarding the aerodynamic characteristics and prediction of high-speed performance are provided.

"A free-flight investigation into the effect of fuselage gloves, or load increases in volume, designed to improve the overall longitudinal area distribution of a swept-wing-body combination revealed that a reduction of about 20 percent in maximum pressure drag was obtained. The drag reduction effected by the use of gloves decreased with increasing Mach number, becoming zero at a Mach number of about 1.35, the limit of the experiments" (p. 1).

Report presenting an investigation of the aerodynamic characteristics of a model of the NACA RM-10 in the hypersonic tunnel at a Mach number of 6.9. Longitudinal pressure surveys were made on the body without fins at zero lift and at angles of attack. Results regarding the pressure distributions, forebody pressure forces, body forces, fin-body combination forces, pitching moment and center of pressure, variation of the zero-lift drag components with Reynolds number and Mach number, variation of the lift-curve slope and center of pressure with Mach number, and Schileren observations are provided.

Memorandum presenting low-lift drag and longitudinal trim data for two versions of an interceptor-type airplane, the second of which had a slimmer nose and a thinner tail than the first. Data are presented for three models (complete, wingless, and horizontal tailless) of the first version, and from one model (complete configuration) of the second version. Results regarding longitudinal trim, drag, longitudinal stability, and flutter and buffet are provided.

Report presenting an investigation in the free-spinning tunnel to determine the effect of lateral-control systems using various combinations of spoilers, slots, and deflectors as compared with ailerons on the spin-recovery characteristics of a model of a 35 degree swept-wing fighter loaded heavily along the fuselage. Testing indicated that the ailerons were favorable for recovery when they were deflected full with the spin. Results regarding the effect of ailerons and two spoiler-slot-deflector configurations are provided.

"The effects of some rivets, butt joints, and lap joints on the drag of a body of revolution at zero lift at supersonic Mach numbers to 2.1 have been obtained in free flight with rocket-propelled models. The butt joints tested showed no significant effects on the drag. Rivets and lap joints increased the drag of the smooth-body configuration, the forward-facing lap joints contributing the greatest increases" (p. 1).

Abstract: "The results of the investigation of three methods of obtaining transverse stability in linear accelerators for ions are presented and discussed. For electric or magnetic quadrupole focusing the range of stable operation, oscillation amplitudes, and the operation of an actual grid is analyzed from measurements of the field distribution. Finally, the formulas applicable to focusing by axial magnetic lenses are presented."

Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distributions in sideslip at six span stations on a 45 degree sweptback, untapered, vertical tail with a 45 degree sweptback horizontal tail mounted at 50-percent and 100-percent vertical-tail span.

Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided.

Abstract: "A simple detector for determining the presence of UF6 in a stream of HF, UF4, and dissociated NH3 is described. The basic detection element is a sensitized piece of carbon rod. The unit has proved satisfactory on production equipment."

From Summary: "Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal tail located well above the extended wing-chord plane indicated static longitudinal instability at moderate angles of attack for all configurations tested. An investigation therefore was made to determine whether the longitudinal stability could be improved by the use of chordwise wing fences, by lowering the horizontal tail, or by a combination of both."

"The external wave drag of bodies of revolution moving at supersonic speeds can be expressed either in terms of the geometry of the body, or in terms of the body-simulating axial source distribution. For purposes of deriving optimum bodies under various given conditions, it is found that the second of the methods mentioned is the more tractable. By use of a quasi-cylindrical theory, that is, the boundary conditions are applied on the surface of a cylinder rather than on the body itself, the variational problems of the optimum bodies having prescribed volume or caliber are solved" (p. 131).

This method essentially consists of analyzing x-ray filtration data in terms of Laplace transforms and obtaining the spectral energy distribution in terms of a sum of the corresponding inverse Laplace transforms. Some of the functions which are especially suited for this application are given and a graphical method of analyzing filtration data in terms of these functions is described. Examples of the practical application of this method to several low energy x-ray machines are included with a discussion of the advantages, disadvantages, and probable uncertainties which are involved.

Report presenting normal-force and pressure distributions for a body of revolution consisting of a fineness-ratio-3, circular-arc, ogival nose tangent to a cylindrical afterbody 7 diameters long. Comparisons of theoretical and experimental distributions indicate that available theoretical methods are only accurate for angles of attack up to about 5 degrees.

Memorandum presenting a comparison made between the incremental aerodynamic root bending moments on the horizontal tail of a jet-powered bomber airplane measured during a flight investigation over a range of Mach numbers and the bending moments calculated by using available theoretical models in conjunction with measured loads, elevator positions, and elevator and stabilizer twists. Results regarding abrupt maneuvers, gradual turn maneuvers, and effects of downwash are provided.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effects of a wing leading-edge modification on the effectiveness of a spoiler-slot-deflector control. The modification consisted of a chord extension over the outboard 35 percent of the semispan in combination with a full-span leading-edge flap deflected 6 degrees.

Report discussing an investigation to determine the aileron effectiveness and damping in roll of the Hughes Falcon missile, D configuration at several Mach numbers. Information about the rolling-moment coefficient, damping-in-roll derivative, and drag coefficient is provided.

Report presenting a free-flight investigation over a range of Mach numbers near zero lift to determine the aileron effectiveness and damping in roll of the full-scale Hughes Falcon missile, D configuration.