Memorandum presenting an investigation conducted with an NACA submerged inlet at Mach numbers from 1.17 to 1.99. Total-pressure ratio, mass-flow ratio, and static pressure distribution along the ramp and main body were obtained at angles of attack of 0 and 6 degrees for a side inlet location. The results showed that the maximum total-pressure ratio attainable with the submerged inlet decreased from 0.83 at a Mach number of 1.17 to 0.52 at a Mach number of 1.99.

Memorandum presenting an investigation of the rolling effectiveness of a partial-span, perforated spoiler on a wing with 45 degrees of sweepback at Mach numbers from 0.25 to 0.96. The effects of the spoiler on the lift, drag, and pitching moment were also determined. Results regarding Reynolds number, Mach number, and predicted rate of roll are provided.

Report presenting an experimental and analytical investigation of the flutter of uniform sweptback cantilever wings. The experiments used groups of wings sweptback by rotating and by shearing with angles of sweep ranging from 0 to 60 degrees. Results regarding the experimental investigation and a discussion and comparison of the analytical and experimental results are provided.

Report discussing an investigation of two 45 degree swept blades in low-speed cascade tunnels at a range of angles of attack and various combinations of inlet-air angle and solidity. The isolated wing method used to design the blade predicted the twist distribution and camber shape necessary to obtain an almost uniform spanwise loading.

A spike-type nose inlet with sharp-lip cowl was investigated at a free-stream Mach number of 2.5 with water injection in its 16-inch diameter, 11-foot-long subsonic diffuser section. Inlet total temperature of exit with liquid-air ratios of about 0.04 with no apparent change in the critical pressure recovery. The observed temperature drops were less than the theoretically predicted values, and the amount of water evaporated was 35 to 50 percent less than that theoretically possible.

The results of power-off force tests and flight tests of a model with a thin unswept low-aspect-ratio wing are presented. The tests were made with the flaps retracted and deflected. The effects on the lateral flight characteristics of decreasing directional stability were noted.

Report presenting an investigation in the transonic tunnel on the effect of sweepback angle on the wing-body characteristics at a range of Mach numbers. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

Report presenting an experimental airplane crash in order to study the performance of a prototype crash-fire inerting system for reciprocating-engine-powered airplanes. A fire did not occur during this crash, indicating that the crash-fire inerting system functioned satisfactorily as a complete unit. Further improvements in the crash-fire system are also provided.

Report discussing an investigation using rocket-propelled vehicles in free flight to determine the effect of fuselage-diameter - wing-span ratio on the damping-in-roll characteristics of delta wings at a range of Mach numbers. The damping-in-roll derivative was found to decrease when the fuselage-diameter - wing-span ratio was increased. The experimental results are compared to calculated values.

Report presenting an experimental investigation to determine some of the characteristics of an inset tab as an aerodynamic balance in the Mach number range between 0.7 and 1.4 using a zero-lift rocket-propelled model in free flight. Results regarding the variation of the aileron floating angle, the wing-tip helix, the balancing effect, and the penalty occurred throughout the Mach number range are provided.

Report presenting the results of static tests conducted for the purpose of determining the lift forces and hinge moments associated with a flat-plate paddle vane, externally hinged near a rocket-nozzle exit and operating on the jet for vane deflection angles ranging from -4 degrees to 25 degrees. Results regarding vane aerodynamic characteristics, performance of rocket motor, and vane erosion

Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.

Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.

Report discussing tests of an unshrouded axial-flow supersonic compressor rotor. Information about the pressure ratio, efficiency, and flow rate with and without inlet guide vanes is provided. The results are also compared to testing on the original shrouded rotor.

Report presenting testing of six 1-series axisymmetrical nose air inlets of 8-inch maximum diameter at zero forward velocity in the 8-foot transonic tunnel. Total-pressure surveys, pressure-recovery measurements, and flow-visualization studies were made through a range of mass-flow ratio from below the normal operating range to choking. Results indicate that the performance characteristics of the inlets with differing amounts of roundness varied widely.

Report presenting an investigation in which the inlet-guide-vane setting of a 10-stage compressor was reduced in order to approximate more closely the design absolute entrance flow angles to the first rotor. In order to determine the effects of these changes, the performance of the inlet stage was obtained simultaneously with the overall compressor performance for both the original and reduced incidence angles. Results regarding the compressor performance, inlet-stage performance, and effect of guide-vane resetting on compressor performance are provided.

Report presenting an investigation of the effects of leading-edge camber without twist on an aspect-ratio-3 delta wing of thickness ratio 3, a body with an ogive nose, and a cylindrical afterbody. Results regarding the base pressures and body characteristics and wing-body combinations are provided.

From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."

This paper contains tail and hull loads data obtained in an investigation of a l/15-scale model of the Goodyear XZP5K airship. Data are presented in the form of tabulated pressure coefficients over a pitch and yaw range of +/-20 deg and 0 deg to 30 deg respectively, with various rudder and elevator deflections. Two tail configurations of different plan forms were tested on the model. The investigation was conducted in the Langley full-scale tunnel at a Reynolds number of approximately 16.5 x 10(exp 6) based on hull length, which corresponds to a Mach number of about 0.12.

Report presenting an investigation of the hydrodynamic characteristics of a model of a 130,000-pound transonic flying-boat design with a high length-beam ratio planing-tail hull, sweptback gull wings with wing-tip floats, and wing-root jet-power-plant installation. Results regarding the aerodynamic, hydrostatic, and hydrodynamic qualities are provided.

"The lateral-directional-stability derivatives of a body in combination with several triangular wings were determined at subsonic and supersonic speeds. The wings used in the investigation were of aspect ratios 2 and 4 and thickness ratios of 3 and 5 percent. One of the wings of aspect ratio 2 was cambered and twisted. The results indicate that at supersonic speeds the effects of plan form on the lateral-directional-stability derivatives for the plane wings were predicted satisfactorily by linearized theory and that the effects of thickness were small" (p. 1).

Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics. Results regarding performance, longitudinal stability, lateral stability, and strakes are provided.

Report discussing testing of two models of the Chance Vought Regulus II missile to determine its drag characteristics for a range of Mach numbers. The measured total-drag-coefficient data was extrapolated to external-drag-coefficient data and presented.

Report presenting an investigation in the 20-inch supersonic tunnel at Mach number 1.92 with a 3.6-inch-diameter ram jet to determine the effects of combustion on the performance of a shock diffuser with a triple-shock projecting cone. Results are presented for a range of outlet areas and fuel flows with both single- and split-fuel-injection systems. Results regarding diffuser performance with combustion, combustion with constant outlet-inlet area ratio, combustion with constant fuel flow, diffuser performance with combustion, and Mach number distribution at the diffuser outlet are provided.