Report presenting an investigation of the aerodynamic characteristics of a four-blade rigid model propeller in the full-scale tunnel for a range of angles of attack, blade angles, and advance ratio. It included a preliminary explanation of vertical descent and a comparison with theory. Results regarding the static thrust and forward flight are provided.

From Summary: "The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA TN 3007."

From Introduction: "Many investigations have been made in the Langley 20-foot free-spinning tunnel in which the natures of airplane spins and recoveries have been determined experimentally with dynamically scaled-down models. The results of some of these investigations are presented in references 1 to 5."

Note presenting the viscosities of five samples of dry-exhaust-gas mixtures at approximately atmospheric pressure and at temperatures from 0 to 1100 degrees Celsius. A method of analysis and correlation proposed by Sutherland has been applied to the data and equations were derived therefrom for representing the results.

Report presenting an investigation to determine the dynamic stability and control characteristics of a cascade-wing vertically rising airplane in the take-off, landing, and hovering phases of flight. It had four propellers with thrust axes parallel to the fuselage axis and distributed along the span so the wings were completely immersed in the stream. Results regarding hovering flight at altitude, hovering flight near the ground, and take-offs and landings are provided.

Report presenting skin-friction measurements for three bodies of revolution of fineness ratio 12.2 with different shapes and pressure distributions: an ogive-cylinder, a cone-cylinder, and a parabolic body. Tests were made at zero angle of attack and over a range of Reynolds numbers based on body length. Results regarding transition and skin friction, surface-temperature surveys, and correlation of pressure-gradient effects are provided.

"A fundamental study of erosion caused by steep pressure waves has been carried out. It is believed that the study gives an insight to the possible causes of damage in high-speed sleeve bearings. In particular, the effect on annealed copper surfaces of steep-fronted pressure waves in oil has been studied, the general conclusion being that cavitation of the oil is the probable cause of damage" (p .1).

Report presenting the effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical airfoil section with a 25-percent-chord plain flap as obtained from wind-tunnel testing at a range of Mach numbers.

From Summary: "The infrared spectra are presented for 47 dicyclic hydrocarbons consisting of some alkyldiphenylmethanes, alkyldicyclohexylmethanes, alkylnaphthalenes, alkyltetralins, 1,3-diphenyl-2-alkylpropanes and 1,3-dicyclohexyl-2-alkylpropanes. The physical properties of these highly purified compounds are included for reference purposes."

Report presenting an investigation of the effects of distributed surface roughness, consisting of lathe-tool marks, on the skin-friction drag of a body of revolution at Mach number 1.61. Tests were conducted on ogive-cylinders at zero angle of attack over a range of roughness and Reynolds number. The results indicate that the effects of surface roughness are generally similar to those found at subsonic speeds.

Report presenting the results obtained in an investigation of the use of rocket-powered models for gust-load studies. A technique for testing in continuous rough air which incorporated the use of a survey airplane evolved.

"Local heat-transfer rates on the surface of a heated flat plate at zero incidence to an air stream flowing at Mach numbers of 1.69 and 2.27 are presented. The Reynolds number range for both Mach numbers was 1 million to 10 million. Surface temperatures were maintained near recovery temperature. It was found that the variation of heat transfer with Mach number was in agreement with previously reported variations of directly measured skin friction with Mach number on unheated bodies" (p. 1).

Report presenting the development of an approximate method for rapid determination of the pressure change for subsonic flow of a compressible fluid under the simultaneous action of heat transfer, friction, rotation, and area change. The report presents the analysis involved in simplifying the momentum equation and the charts necessary for obtaining particular solutions.

A procedure proposed for use in the design of air-heated systems for the continuous prevention of ice formation on airplane components is set forth. Required heat-transfer and air-pressure-loss equations are presented, and methods of selecting appropriate meteorological conditions for flight over specified geographical areas and for the calculation of water-drop-impingement characteristics are suggested. In order to facilitate the design, a simple electrical analogue was devised which solves the complex heat-transfer relationships existing in the thermal-system analysis.

Note presenting an investigation of the effects of the firing time and the weight of nickel deposited from the nickel-dip solution on the adherence developed by a cobalt-free and a cobalt-bearing ground-coat enamel on both enameling iron and a titanium-bearing low-carbon steel. Results regarding the effect of nickel dip on adherence, effect of nickel dip on fishscaling, effect of nickel dip on oxidation of steel, nickel remaining on steel after various firing treatments, and effect of nickel dip on appearance of enamel-metal interface are provided.

Report presenting the total zero-lift drag of a fin-stabilized parabolic body of revolution designated the RM-10 using scale models launched from a gun through still air at a range of Mach and Reynolds numbers. Results indicated that the location of transition had an important effect on the drag of the configuration.

Note presenting a study of existing experimental and theoretical results for an inclined flat plate of infinite span, and of the extent to which the results are indicative of those for thin airfoil sections. The study included an examination of the flow about an inclined plate, the forces on the plate, and the adequacy of theory in predicting the forces. The results indicate that there are two important ranges of angle of attack differing by the extent of flow separation on the upper surface.

From Summary: "Tables and computing instructions are presented for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ratio of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges."

Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges.

Note presenting tests performed on 21 sheet-stringer panels of 75S-T6 aluminum alloy with alclad sheets nominally 0.051 inch thick and stringers nominally 3.5 inches apart. Three panels of different types, with five stringers each and overall dimensions of approximate 18 by 15 inches, were tested in axial flat-end compression. Results regarding the flat-end compression, protruding-stringer compression, and bending are provided.

Report presenting the application of time-temperature parameters to stress-strain, rupture, and creep data for metals and alloys. A parameter based on rate-process theory was successfully applied to rupture and creep data for aluminum and various aluminum alloys.