Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stability derivatives, and a single support strut on the stability, control, and aerodynamic characteristics.

Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.

Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.

"An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner fuel-air ratios at diffuser-inlet total pressures from 2750 to 620 pounds per square foot" (p. 1).

Report presenting a small-scale transonic investigation of a semispan wing sweptback 45 degrees and of aspect ratio 4 with combinations of nose-flap deflections and wing twist in the high-speed 7- by 10-foot tunnel over a range of Mach numbers. Lift, drag, and pitching-moment data were obtained for several different configurations.

Report presenting pressure measurements on a semispan model of a cambered and twisted wing, alone and in combination with a fuselage. The wing had 40 degrees of sweepback, an aspect ratio of 10, a taper ratio of 0.4, and 5 degrees of washout at the tip. Results regarding the pressure distribution and flow separation, section characteristics, and span loading characteristics are provided.

Memorandum presenting a comparison of the aerodynamic characteristics and flow phenomena at transonic speeds for a 45 degree sweptback wing mounted alternatively on a cylindrical body and an indented body. Indentation eliminated the zero-lift drag rise associated with the wing at a Mach number of 1. Results regarding the lift, drag, and pitching moment, flow surveys, level-flight characteristics, and flow phenomena are provided.

Report presenting information on the amount and relative intensity of atmospheric turbulence for altitudes up to 60,000 as obtained by airplanes and balloon-borne instruments. Analysis of the data obtained indicated that there are substantial reductions in turbulence at higher altitudes in the weather conditions measured in the tests. Results regarding gust distributions, including non-thunderstorm turbulence, thunderstorm turbulence, total gust distributions, and a comparison of gusts are also provided.

Report presenting an investigation in an altitude test chamber to determine criteria for the design of flame holders for a turbojet-engine afterburner. The performance of ten flame holders was obtained in a louvered-liner afterburner operated at constant afterburner-inlet temperature over a range of fuel air ratio and total pressures. Results regarding the effect of gutter cross-sectional shape, effect of gutter width, effect of flame-holder blocked area, effect of trailing and interconnecting gutters, and effect of altitude on V-gutter flame holders are provided.

From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."

Report presenting measurements of average heat-transfer and friction coefficients for air flowing through a smooth, electrically heated tube with a bellmouth entrance with a length-to-diameter ratio of 15 and a range of average surface temperatures, Reynolds numbers, exit Mach numbers, and heat fluxes. Results regarding the axial-wall-temperature distribution, heat balance, correlation of heat-transfer coefficients, and correlation of friction coefficient are provided.

Report presenting spanwise lift distributions, lift coefficients, spanwise centers of pressure, shifts in aerodynamic center, coefficients of damping in roll, aileron rolling-moment coefficients, and rates of steady roll per unit aileron deflection have been calculated for nine M-, W-, and delta wings, as well as for comparable ordinary sweptforward, unswpet, and sweptback wings. Certain qualitative conclusions are drawn concerning the plan forms most suitable from the aeroelastic point of view. M and W plan forms exist which are superior aeroelastically and structurally to ordinary swept wings.

Report presenting an approximate inverse impeller design procedure based on the assumption of axisymmetric, nonviscous flow along with some limited experimental data obtained from a high solidity, 12-inch transonic impeller. The design procedure includes a point-by-point solution of the impeller flow conditions along a series of streamlines in the radial-axial plane. Results regarding the overall performance, impeller flow limits, and blade structural failure are provided.

Report presenting the effects of flame-immersed blades on combustion stability and efficiency, which were determined at various combustor-inlet conditions by use of several geometric blade arrangements, two fuels, two fuel-injection systems, and two blade temperatures. Specific combustor configurations with flame-immersed blades showed marked improvement in stability and efficiency. The operational life of the blades was also observed to be excellent.

From Introduction: "An investigation of the variation in turbine-entrance equivalent weight flow for a two-stage turbine equipped with an adjustable turbine stator is presented in reference 1. A general analytical investigation of turbine stator adjustment is presented in reference 2. In reference 2, the effect of stator adjustment on turbine off-design performance is also investigated by analytically computing the performance of a particular single-stage turbine."

Memorandum presenting measurements of the oscillatory lift force acting on an airfoil vibrated in bending. Results were obtained for an isolated airfoil and for the same airfoil oscillated in a cascade, at low and high angles of attack.

Report presenting an extension of NACA RM A52C14 about inlet design and performance for Mach numbers of 1.5 to 2.0. A two-dimensional inviscid analysis is used to compare the performance of several types of inlets when used in conjunction with a turbojet engine with constant-volume air flow. Results regarding air delivery and air requirements, drag factors, evaluation of inlet performance, significance of the drag summation, and inlet and engine-matching considerations are provided.

A study of the effects of variations in lateral-oscillatory characteristics on air-to-air tracking performance has been made, using a conventional, propeller-driven fighter airplane equipped with servo devices for varying these characteristics in flight. Tracking runs were made both in smooth air and in simulated rough air. The lateral-oscillation period, damping, and roll coupling were varied over wide ranges during the investigation.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a body-control arrangement at Mach number 1.61. A 70 degree delta canard-type control mounted in the horizontal plane and with a span-to-body-diameter ratio at the control trailing edge of 2.52 tested both fixed and moving in the presence of a long cylindrical body with a parabolic nose.

Report presenting an investigation in a duct system with fully developed pipe flow to determine the effects of vortex generators on the performance of a diffuser with whirling inlet flow. Testing was made with three different inlet whirl angles and rectangular, noncambered airfoils that varied in chord, span, angle setting, number, and location. Results for the 20.6 degree inlet whirl angle, 15.2 degree inlet whirl angle, 0 degree inlet whirl angle, and effect of inlet whirl angle on diffuser performance are provided.

Report presenting an investigation of the total-pressure-recovery characteristics over a wide range of angles of attack of an axially symmetric nose inlet at a Mach number of 1.42 and an asymmetric nose inlet at Mach numbers of 1.42 and 1.84.

Report presenting testing of a ram-jet canard missile model with a wing and horizontal and vertical canard surfaces of delta plan form with 70 degree swept leading edges in the supersonic pressure tunnel. Two ram-jet nacelles were mounted in the vertical plane near the rear of the body and various combinations of components were tested. Results regarding the longitudinal and lateral characteristics, comparison with theory, and effect of nacelles on the model are presented.

From Introduction: "A theoretical investigation was conducted in order to determine what effect the differences in aerodynamic characteristics would have on the short-time response to elevator control of this type of airplane as compared with the responses of a conventional airplane, without regard to any possible psychological influences. The results of this investigation are presented in this paper."

Report presenting an investigation to determine the effect of circumstantial inlet location on the performance of twin half-conical scoop-type inlets with and without boundary-layer removal at several Mach numbers and angles of attack. For positive angles of attack, higher pressure recovery performance was obtained with the inlets mounted on lower fuselage quadrants than on upper quadrants.