Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.

Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.

Report presenting a method for calculating the lift and pitching-moment characteristics of circular cylindrical bodies in combination with triangular, rectangular, or trapezoidal wings or tails through the subsonic, transonic, and supersonic speed ranges. A computing table and set of design charts are presented to reduce the calculations to routine operations. Information about lift, center of pressure, effects of wing incidence, and limitations and extensions of the method is provided.

Report presenting an investigation at transonic speeds using the wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a 1/30-scale semispan model of the Bell X-5 airplane with three different degrees of sweepback. Lift, drag, and pitching moment are presented for various angles of attack for several horizontal-tail settings and with the tail off for each angle of sweep tested.

Report presenting testing of three scale models and a full-scale configuration of systems for ducting cooling air through a turbojet engine tail cone to a cooled turbine rotor in order to determine pressure-loss characteristics.

From Introduction: "The investigation reported herein, which was conducted in an NACA Lewis altitude test chamber, covered a range of altitudes from 30,000 to 50,000 feet at a flight Mach number of 0.8."

An investigation was conducted to determine the behavior of recently produced, forged S-816 turbine blades in a full-scale turbojet engine, and in particular, the scatter in performance of the alloy. The turbine blades were operated as continuously as possible at a temperature of 1500 degrees F and a centrifugal stress of 21,500 pounds per square inch. The operating lives of the turbine blades varied from 181 to 539 hours, a range of 358 hours. Stress-rupture properties of specimens cut from blade airfoils also varied considerably, as much as 1257 hours at 20,000 pounds per square inch and 1500 degrees F. Since the variability of scatter of stress-rupture data is greater than that of blade performance, the scatter is probably caused by variations in the properties of the forged blades rather than by variations caused by engine operation or installation of the blades. Metallographic examinations were made to determine possible causes of the scatter and although numerous differences in microstructures of blades were found, no consistent tendencies were observed and the findings did not permit an explanation of the scatter of blade performance. The results of the metallographic examinations and of the physical tests indirectly indicated variables in the fabricating method …

Report presenting an experimental investigation in the 8- by 6-foot supersonic wind tunnel to determine the performance characteristics of a twin-duct side intake system joining into a common duct and utilizing two-dimensional 6 degree compression ramps mounted on a supersonic airplane at Mach numbers 1.5 and 1.7.

"A method is presented for estimating the rolling moments caused by wing-tail interference for missiles composed of wing-tail-body combination. The considerations involved in determining the structure of the downwash field behind lifting cruciform wing-body combinations and the rolling moment on cruciform wings of various plan forms induced by an infinite line vortex are discussed in detail. Computations of induced rolling moments for several missile designs are compared with experimental results" (p. 1).

An investigation of the performance of a twin-duct air-intake system with a 9 degree compression-ramp inlet mounted on a supersonic airplane in the 8- by 6-foot supersonic wind tunnel at a range of Mach numbers, angles of attack, yaw, and mass-flow ratios. The effect on performance of a series of boundary-layer-removal wedges and a main-duct airflow bypass system were also investigated.

Report presenting an experimental investigation in the altitude test chamber on an axial-flow turbojet engine at transonic flight conditions to determine the magnitude of thrust augmentation and to ascertain the operational characteristics of a combined augmentation system. Results regarding the augmented engine performance, influence of coolant on afterburner combustion, performance losses, and operational problems are provided.

The adhesive and protective characteristics of National Bureau of Standards Coating A-417 were investigated, as well as the effect of the coating on the life of forged Refractaloy 26 and cast Stellite 21 turbine blades. Coated and uncoated blades were run in a full-scale J33-9 engine and were subjected to simulated service operations consisting of consecutive 20-minute cycles (15 min at rated speed and approximately 5 min at idle). The ceramic coating adhered well to Refractaloy 26 and Stellite 21 turbine blades operated at 1500 degrees F. The coating also prevented corrosion of the Refractaloy 26, a corrosion-sensitive nickel-base alloy, and of the Stellite 21, a relatively corrosion-resistant cobalt-base alloy. Although the coating prevented corrosion of both alloys, it had no apparent effect on blade life.

Memorandum presenting an investigation conducted to determine the effects of spinner shape on the pressure-recovery characteristics of an NACA 1-series D-type cowl operating behind a three-blade single-rotation propeller. Two spinner shapes were considered, an NACA 1-series spinner and a modified spinner, more nearly conical than the 1 series.

From Introduction: "This report extends the short-bearing pressure-distribution function of Michell and Cardullo to give equations for the various bearing characteristics. This short-bearing approximation makes available formulas relating eccentricity ratio to applied load, attitude angle, angular position of peak film pressure to unit pressure on projected area."

Report presenting the effect of external fuel tanks and externally mounted rocket packets on the drag characteristics of a model of a tailless fighter airplane. Lift, drag, pitching-moment, and rolling-moment coefficients and lift-drag ratios are presented in tabular form and the drag characteristics and lift-drag ratios are also presented in graphic form.

"A low-speed investigation was made of a 1/6-scale model of the Republic XF-84H airplane. The model had a single tractor propeller and a 40 degree swept wing of aspect ratio 3.45. This investigation was undertaken to provide information on the effects of propeller operation on longitudinal stability characteristics for the XF -84H airplane and to provide an indication of slipstream effects that might be encountered on similar swept-wing configurations" (p. 1).