Report presenting the flutter characteristics of an untapered, 45 degree sweptback, aspect-ratio-4 wing at a range of Mach numbers. The results from NACA RM L55E19a are included along with additional information regarding the models, the tests, and the results of the flutter calculations.

"A study of the high-temperature oxidation of several aircraft construction materials was undertaken to assess the possibility of ignition under high-temperature flight conditions.Tests have been made both in open and closed jets, and, in addition, the burning of metals has been observed under static conditions in a pressurized vessel containing either air, oxygen, or nitrogen. When heated in an atmosphere of oxygen or when heated and plunged into a supersonic airstream, titanium, iron, carbon steel, and common alloys such as 4130 were found to have spontaneous-ignition temperatures in the solid phase (below melting) and they melted rapidly while burning" (p. 1).

Report presenting side-force and directional-stability characteristics of four airplane-like configurations determined at a range of Mach numbers and angles of sideslip at zero angle of attack. Two configurations had trapezoidal wing and tail surfaces and two had triangular wing and tail surfaces. The directional stability of the configurations generally decreased with increasing Mach number.

Report presenting a theoretical study of the possibility of improving the lifting efficiency of aircraft flying at supersonic speeds using indirect lift, which can be induced on the wing by the fuselage shape and/or wing end plates. Results indicated that lifting efficiency of a planar wing may be improved by favorable interference induced by lateral forces on the end plates or on the sides of the fuselage.

Report presenting a free-flight investigation of the control effectiveness of a differentially deflected horizontal tail. The results were compared with and found to be in general agreement with estimates derived from other free-flight tests, wind tunnel tests, and theory. Results regarding the rolling moment, yawing moment, and overall rolling effectiveness are provided.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel at a range of Mach numbers to determine the aerodynamic loads on finned and unfinned bodies in the presence of a swept wing. A tip-mounted body at 1.04 semispan and an underwing pylon-mounted body at 0.33 semispan were investigated. Results regarding the body loading characteristics and effect of angle of attack are provided.

Report presenting an investigation of the aerodynamic characteristics of various configurations of a model of the Republic F-105 in the transonic tunnel at a variety of Mach numbers. Results regarding lift characteristics, pitching-moment characteristics, zero-lift drag characteristics, maximum lift-drag ratio, flaperon and rudder characteristics, and effective downwash characteristics are provided.

Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.

Report presenting measurements of aerodynamic heat transfer at six stations on the 40-inch-long 10 degree total-angle conical nose of a rocket-propelled model at Mach numbers up to 5.9. Laminar, transitional, and turbulent heat-transfer coefficients were obtained for Mach numbers up to 4. Results regarding skin temperature time histories, boundary-layer transition, and calculated skin temperature are provided.

Memorandum presenting an application of the supersonic area rule concept to the deign of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. The pressure drag from the configuration with nacelles was found to be significantly less than that from a corresponding configuration without nacelles throughout the Mach number range.

Results presenting an investigation in the supersonic pressure tunnel to determine the static stability and control characteristics of a ram-jet canard missile at Mach number 2.01. The missile had wings, canard surfaces of delta plan form with 70 degree swept leading edges, and two ram-jet nacelles. Results regarding the longitudinal and lateral characteristics are provided.

Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided.

Memorandum presenting the optical transmission characteristics of turbulent boundary layers in air on a flat plate with negligible heat transfer measured photometrically for ranges of Mach number from 0.4 to 2.5. The results indicated that the scattering from a collimated beam of white light which penetrates a turbulent boundary layer depends mainly on the integral across the layer of the difference between the free-stream density and the local boundary-layer density.

Memorandum presenting a generalized analysis of a pressure-jet powerplant. The effect of changes in ambient conditions on the powerplant performance is provided in a series of charts using parameters containing temperatures and pressures. Some of the variables investigated included the pressure-jet powerplant performance in helicopter and pressure-jet-helicopter performance.

Report presenting an investigation in the 8- by 6-foot supersonic tunnel to determine the external-stream effects on the gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers. Results regarding the pumping, thrust, and base characteristics, boattail drag characteristics, and stream effects on jet thrust for typical ejector installations are provided.

"Flight tests of fifteen T-231 70-mm HEAA rocket projectiles (flight components of the T-263 HEAA rounds) were made at the Langley Pilotless AIrcraft Research Station at Wallops Island, VA., to obtain flight trajectories at high quadrant elevation launchings and to obtain drag data. Although all rounds were of the same general type, there were differences in nozzle cant angles, number of nozzles per round, shape of head and fuse, motor case length, and type of propellant. All projectiles were launched at an elevation angle of 60 deg" (p. 1).

Report presenting a study of injection principles for liquid oxygen and heptane made with two-element injectors, as the previous study only included single-element injectors. Eight injectors, produced by two spray orientations of each of the four injection processes, were investigated. Results regarding atomization after mixing, atomization before mixing, atomization without mixing, fuel atomization without mixing, and overall comparisons of the injectors are provided.

Report presenting the use of a hot-wire anemometer to study the tip-region flow phenomena at the exit of a single-stage transonic compressor rotor. The flow phenomena were recorded as a film which is available as a supplement to the report. Results regarding overall results of hot-wire measurements, quantitative results from hot-wire measurements, and some concluding remarks are provided.

"The stability of systems containing a heat source is examined from the energy point of view. Rayleigh's criterion is derived. In the case of a flame, it is found that Rayleigh's criterion must be modified slightly if the specific-heat ratios of the burned and unburned gases are different" (p. 1).

Report presenting an investigation of the intensity of root-mean-square pressure pulsations and root-mean-square normal-force-coefficient fluctuations conducted on two high-lift airfoils and two 6-series airfoils. Results regarding the factors affecting comparison of data from various test facilities, root-mean-square pressure pulsations, and root-mean-square force fluctuations are provided.

Memorandum presenting an investigation at Mach numbers of 1.61 and 2.01 to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results regarding pressure distributions, spanwise loadings, and integrated coefficients are provided.

Report presenting an investigation at two Mach numbers to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results of the tests indicated that the incremental pressure distributions due to spoiler were in agreement with previous results as long as the spoiler was not too close to a break in the wing surface or the wing tip.

Report presenting zero-lift drag data obtained on a series of six bomb shapes. Five configurations had the same body shape with different body-surface conditions and profile and plan form of fins, and the sixth had a different and longer body shape. Results regarding the effect of blunt trailing edge, blunt leading edge, fin thickness, and body surface are provided.

Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.