Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The store was separately sting-mounted on its own six-component internal balance and was traversed through a wide systematic range of spanwise, chordwise, and vertical positions.

Report presenting a full-scale, free-jet investigation to determine the performance of a side-inlet supersonic diffuser designed for a flight Mach number of 2.75. Several internal modifications made to improve diffuser-outlet flow uniformity were also evaluated. Results regarding the general characteristics of the diffuser and effect of diffuser modifications on flow distribution are provided.

"A dye-tracer technique has been developed whereby the quantity of dyed water collected on a blotter-wrapped body exposed to an air stream containing a dyed-water spray cloud can be colorimetrically determined in order to obtain local collection efficiencies, total collection efficiency, and rearward extent of impingement on the body. In addition, a method has been developed whereby the impingement characteristics obtained experimentally for a body can be related to theoretical impingement data for the same body in order to determine the droplet size distribution of the impinging cloud. Several cylinders, a ribbon, and an aspirating device to measure cloud liquid-water content were used in the studies presented herein for the purpose of evaluating the dye-tracer technique" (p. 1).

Report presenting the results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model with a Mach number of 2.01. Results regarding the effect of adapter shape and aerodynamic characteristics of the model alone are provided.

From Introduction: "This report presents the results of an analytical study made to determine the accuracy with which several commonly used averaging or weighting methods reproduce the real flow properties."

Note presenting several recent advances in plane subsonic flow theory combined into a unified second-order theory for airfoils of arbitrary shape. The solution is reached in three steps. Solutions for a number of airfoils are given and are compared with the results of other theories and of the experiment.

Report presenting experimental measurements of average skin friction of the turbulent boundary layer on free-flying, hollow-cylinder models at four Mach numbers at conditions of high rates of heat transfer. The data of the investigation indicates that increasing skin-friction ratio with increasing heat-transfer rates will persist up to Mach numbers as high as 7. Results regarding skin-friction ratio and the T' method for evaluating skin friction are provided.

From Introduction: "References 1 and 2 indicate that the sea-level static thrust of a centrigual-flow-type turbojet engine may be increased about 25 percent by use of liquid injection. Reference 3 indicates that greater thrust augmentation is possible at a compressor pressure ratio of 11 than of 4."

Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. Results regarding variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shapes, variation of base pressure with Mach number, and correlation of base pressure data are provided.

Note presenting a study of the laminar compressible boundary layer induced by a shock wave advancing into a stationary fluid bounded by a wall. Velocity and temperature profiles, recovery factors, and skin-friction and heat-transfer coefficients are tabulated for a wide range of shock strengths.

Report presenting a rapid approximate method for the design of centrifugal compressors of given blade shape with compressible nonviscous flow characteristics. The method was applied to the design of an impeller to determine the approximate maximum meridional streamline spacing that could be used. Results regarding shroud profile, velocity ratio, blade surface velocities, and inlet angle of attack are provided.

Note presenting the use of small-perturbation spectral-analysis techniques 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.

Report presenting a re-evaluation of the experimental data of liquid-metal heat-transfer characteristics using the most consistent assumptions and methods as possible and then compared with each other and with theoretical results.

Report presenting a method that can be used to predict either the local permeability necessary for a prescribed distribution of the coolant flow or the coolant-flow distribution resulting from a prescribed local permeability. It is applied to a determination of conditions in rotating turbine blades with transpiration-cooled walls.

Report presenting handling-quality flight tests using an SB2C-5 drone under radio remote control from an F6F-5 control plane. Similar tests were conducted with the drone under manual control. The beep-type, remote-control system investigated was generally satisfactory for flight testing an airplane via remote control, including take-off and landings.

A method of strength analysis of short sheet-stringer panels subjected to compression is presented which takes into account the effect that the riveted attachments between the plate and the stiffeners have on the strength of the panels. An analysis of experimental data shows that panel strength is highly influenced by rivet pitch, diameter, and location and that the degree of influence for a given riveting depends on the panel configuration and panel material. (author).

Report presenting an investigation in the free-flight tunnel to determine the static stability characteristics of several fuselages with a relatively flat cross section and a high fineness ratio. Results regarding the fuselages alone and fuselages with various vertical and horizontal surfaces are provided.

A simplified procedure is shown for calculating the once-per-revolution oscillating aerodynamic thrust loads on propellers of tractor airplanes at zero yaw. The only flow field information required for the application of the procedure is a knowledge of the upflow angles at the horizontal center line of the propeller disk. Methods are presented whereby these angles may be computed without recourse to experimental survey of the flow field. The loads computed by the simplified procedure are compared with those computed by a more rigorous method and the procedure is applied to several airplane configurations which are believed typical of current designs. The results are generally satisfactory.

A method for the solution of the incompressible nonviscous flow through a centrifugal impeller, including the inlet region, is presented. Several numerical solutions are obtained for four weight flows through an impeller at one operating speed. These solutions are refined in the leading-edge region. The results are presented in a series of figures showing streamlines and relative velocity contours. A comparison is made with the results obtained by using a rapid approximate method of analysis.

"The problem of a jet-propelled airplane held in a steady turn is treated both in the very general case and also in the particular case when the polar curve can be approximated by a parabola. Once the general solution has been obtained, some typical maneuvers are next studied such as, the turn of maximum bank, of maximum angular velocity, and of minimum radius of curvature. After a brief comparison is made between the turning characteristics of conventional airplanes and jet airplanes, and after the effect of compressibility upon the turn is examined, the effects of the salient aerodynamic and structural parameters upon the behavior of the plane in curvilinear flight are summarized in the conclusions" (p. 1).

From Summary: "Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their motion and aerodynamic heating in unpowered flight. Powered flight is analyzed for an idealized propulsion system which rather closely approaches present-day rocket motors. Unpowered flight is characterized by a return to earth along a ballistic, skip, or glide trajectory. Only those trajectories are treated which yield the maximum range for a given velocity at the end of powered flight. Aerodynamic heating is treated in a manner similar to that employed previously by the senior authors is studying ballistic missiles (NACA RM A53D28), with the exception that radiant as well as convective heat transfer is considered in connection with glide and skip vehicles."

"The steady-state over-all performance characteristics of the J65-B3 turbojet engine were determined in an altitude test chamber for four exhaust-nozzle areas at Reynolds number indices of 0.8, 0.4, and 0.2. This range of Reynolds number indices corresponds to a range of altitudes from about sea level to 51,500 feet at a flight Mach number of 0.8. Generalized data are presented to allow calculation of engine performance at any flight condition corresponding to a Reynolds number index within the range investigated" (p. 1).

"For a period of ten to fifteen years intensive research and development has been conducted on turbojet propulsion systems for aircraft. During this period much has been learned about the system both from the standpoint of current usage and of future development possibilities. It is the purpose of this report to discuss the current status of the turbojet engine as produced in the United States and to discuss the future possibilities for improvement in the engine and in the fuel. The engine and fuel improvements will be evaluated both from the standpoint of probability of success in obtaining these improvements and from the standpoint of the effects of these improvements on the airplane performance" (p. 1).

"Spatial burnout calculations have been made of two types of water moderated cylindrical reactor using boron as a burnable poison to increase reactor life. Specific reactors studied were a version of the Submarine Advanced Reactor (sAR) and a supercritical water reactor (SCW). Burnout characteristics such as reactivity excursion, neutron-flux and heat-generation distributions, and uranium and boron distributions have been determined for core lives corresponding to a burnup of approximately 7 kilograms of fully enriched uranium" (p. 1).