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Mixture Distribution in a Single-Row Radial Engine

Description: "The distribution of the fuel among the various cylinders of a Pratt and Whitney 1340 S1H1-G engine was determined by chemically analyzing samples of exhaust gas from each cylinder. The engine was operated in the 20-foot wind tunnel at different power outputs, specific fuel consumptions, and engine speeds. The results showed that the variation in the quality of the mixture among the different cylinders was approximately 4 percent and was independent of power output, specific fuel consumption, a… more
Date: October 1936
Creator: Gerrish, Harold C. & Voss, Fred
Partner: UNT Libraries Government Documents Department
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A study of factors affecting the steady spin of an airplane

Description: Data from wind-tunnel tests on a model of the NY-1 airplane were used in a study of the effect on the steady spin of a number of factors considered to be important. The factors were of two classes, mass distribution effects and aerodynamic effects. The study indicated that mass extended along the longitudinal axis has no detrimental effect or is even slightly beneficial, mass extended along the lateral axis is detrimental if the airplane spins with the inner wing tip far down, and mass extended… more
Date: August 1933
Creator: Scudder, Nathan F.
Partner: UNT Libraries Government Documents Department
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Tests in the gust tunnel of a model of the XBM-1 airplane

Description: Report presenting testing of a dynamically scaled model of a Navy XBM-1 biplane in the gust tunnel to provide data for use in determining the structure of atmospheric gusts from measurements of the motions of the full-scale airplane in rough air. Records for two flights for several gradients were evaluated to give histories of events during passage through the gust.
Date: October 1939
Creator: Donely, Philip & Shufflebarger, C. C.
Partner: UNT Libraries Government Documents Department
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General tank tests of a 1/10-size model of the hull of the Boeing XPBB-1 flying boat - Langley Tank Model 175

Description: Report presenting general tank tests of a scale model of the hull of the Boeing XPBB-1 flying boat in tank no. 1. Testing occurred on the forebody alone, the forebody with the afterbody, and the forebody with the afterbody and tail extension, which represented the complete hull. Results regarding the resistance, trimming moment, and length of the planing bottom wetted by the water are provided.
Date: July 1946
Creator: King, Douglas A. & Hill, Mary B.
Partner: UNT Libraries Government Documents Department
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The Synthesis and Purification of Aromatic Hydrocarbons 5: 1-Ethyl-3-Methylbenzene

Description: "The method used for the synthesis and purification of an 8-gallon quantity of 1-ethyl-3-methylbenzene from m-creosol consists in obtaining m-methylcyclohexanone from m-creosol by hydrogenation followed by oxidation, condensation of the ketone with ethylmagnesium bromide, dehydration of the tertiary alcohol obtained, and the dehydration of the olefins to 1-ethyl-3-methylbenzene. A yield of 28 percent of the theoretical was obtained from 98 percent commercial m-creosol. The physical properties o… more
Date: November 1946
Creator: Ebersole, Earl R.
Partner: UNT Libraries Government Documents Department
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The Synthesis and Purification of Aromatic Hydrocarbons 4: 1,2,3-Trimethylbenzene

Description: "A six gallon quantity of 1,2,3-trimethylbenezene was prepared and purified in a four-step synthesis involving the condensation of 1,3-pentadiene with crotonaldehyde. The dimethylcyclohexencarboxaldehydes formed were hydrogenated to give the corresponding isomeric dimethylcyclohexylcarbinols. The dehydration of the carbinols and the subsequent dehydrogenation of the trimethylcyclohexenes yielded the 1,2,3-trimethylbenzene. The overall yield was 24 percent; the physical properties of the materia… more
Date: November 1946
Creator: Lamberti, J. M.; Reynolds, T. W. & Chanan, H. H.
Partner: UNT Libraries Government Documents Department
open access

A general tank test of a model of the hull of the Pem-1 flying boat including a special working chart for the determination of hull performance

Description: The results of a general tank test of a 1/6 full-size model of the hull of the P3M-1 flying boat (N.A.C.A. model 18) are given in non-dimensional form. In addition to the usual curves, the results are presented in a new form that makes it possible to apply them more conveniently than in the forms previously used. The resistance was compared with that of N.A.C.A. models 11-C and 26(Sikorsky S-40) and was found to be generally less than the resistance of either.
Date: December 1938
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department
open access

Tanks test of a model of the hull of the Navy PB-1 flying boat - N.A.C.A. Model 52

Description: A model of the hull of the Navy PB-1 flying boat was tested in the N.A.C.A. tank as part of a program intended to provide information regarding the water performance of hulls of flying boats of earlier design for which hydrodynamic data have heretofore been unavailable. Tests were made according to the general method over the range of practical loadings with the model both fixed in trim and free to trim. A free-to-trim test according to the specific method was also made for the design load and … more
Date: August 1936
Creator: Allison, John M.
Partner: UNT Libraries Government Documents Department
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Comparative Performance Obtained With XF7C-1 Airplane Using Several Different Engine Cowlings

Description: Discussed here are problems with the use of cowlings with radial air cooled engines. An XF7C-1 airplane, equipped with service cowling and with narrow ring, wide ring, and exhaust collector ring cowlings over the service cowling, was used. For these four cowling conditions, the rate of climb and high speed performance were determined, the cylinder conditions were measured, and pictures to show visibility were taken. The level flight performance obtained with an engine speed of 1900 r.p.m. for t… more
Date: February 1930
Creator: Schey, Oscar W.; Johnson, Ernest & Gough, Melvin N.
Partner: UNT Libraries Government Documents Department
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Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 0-1HTA Magnesium Alloy

Description: Column and plate compressive strengths of extruded 0-1HTA magnesium alloy were determined both within and beyond the elastic range from tests of flat end H-section columns and from local instability tests of H-, Z-, and channel section columns. These tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircr… more
Date: January 1947
Creator: Heimerl, George J. & Niles, Donald E.
Partner: UNT Libraries Government Documents Department
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Flight Tests of N.A.C.A. Nose-Slot Cowlings on the BFC-1 Airplane

Description: "The results of flight tests of four nose-slot cowling designs with several variations in each design are presented. The tests were made in the process of developing the nose-slot cowling. The results demonstrate that a nose-slot cowling may be successfully applied to an airplane and that it utilizes the increased slipstream velocity of low-speed operation to produce increased cooling pressure across the engine" (p. 1).
Date: August 1939
Creator: Stickle, George W.
Partner: UNT Libraries Government Documents Department
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Bonding Strengths of Adhesives at Normal and Low Temperatures

Description: Note presenting a determination of the bonding strengths of two thermosetting adhesives, liquid Cycleweld C-3 and Ardux 1, to several aircraft materials using shear tests made on lap-joint specimens. The specimens were tested at 25 degrees Celsius and at subfreezing temperatures of approximately -40 degrees Celsius. Results regarding the specimens bonded under clamping pressure, specimens bonded after various surface treatments, specimens of metal bonded to plywood, and specimens of aluminum bo… more
Date: January 1945
Creator: Axilrod, B. M. & Jirauch, D. H.
Partner: UNT Libraries Government Documents Department
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Notes and Tables for Use in the Analysis of Supersonic Flow

Description: Paper presenting a compilation of formulas, tables, and curves that have been found to be useful in the analysis of supersonic wind-tunnel data.
Date: December 1947
Creator: The Staff of the Ames 1- by 3-foot Supersonic Wind-Tunnel Section
Partner: UNT Libraries Government Documents Department
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Correlation of physical properties with molecular structure for dicyclic hydrocarbons : I -2-n-alkylbiphenyl, 1,1-diphenylalkane,a,w-diphenylalkane; 1,1-dicyclohexylalkane, and a,w-dicyclohexylalkane series

Description: Report presenting a study of the correlation between molecular structure and physical properties of high-density hydrocarbons, including the net heat of combustion, melting point, boiling point, density, and kinematic viscosity. They are evaluated for their use as a fuel, especially in planes that are required to have smaller fuel tanks.
Date: May 1950
Creator: Wise, Paul H.; Serijan, Kasper T. & Goodman, Irving A.
Partner: UNT Libraries Government Documents Department
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Density fields around a sphere at Mach numbers 1.30 and 1.62

Description: From Summary: "Interferograms were taken of the flow around a sphere at Mach numbers of 1.30 and 1.62. The results of the evaluation of these interferograms are shown as plots of contours of constant density ratio in the flow field around the sphere and as the distribution of flow variables along the axis of symmetry between the shock wave and the sphere. In appendixes the theory of the analysis is reviewed, sources of error are discussed, and the detailed procedure used in the evaluation of in… more
Date: August 1950
Creator: Gooderum, Paul B. & Wood, George P.
Partner: UNT Libraries Government Documents Department
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Free-jet tests of a 1.1-inch-diameter supersonic ram-jet engine

Description: Results are presented of free-jet tests of a 1.1-inch-diameter hydrogen-burning ram-jet engine over a Mach number range from 1.42 to 2.28 and a Reynolds number range from 6.01 times 10 to the 6th power to 15.78 times 10 to the 6th power. Tests demonstrated the reliability and wide operating range of the engine and showed its suitability for installation on wind-tunnel models of airplane and missile configurations. A comparison of engine operation with combustion-chamber lengths of 3.33 and 1.51… more
Date: February 1957
Creator: Judd, Joseph H. & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department
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Preliminary wind-tunnel tests of triangular and rectangular wings in steady roll at Mach numbers of 1.62 and 1.92

Description: Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92.
Date: June 1956
Creator: Brown, Clinton E. & Heinke, Harry S., Jr.
Partner: UNT Libraries Government Documents Department
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Impingement of Water Droplets on NACA 65(1)-208 and 65(1)-212 Airfoils at 4 Degrees Angle of Attack

Description: "The trajectories of droplets in the air flowing past NACA 65(1)-208 airfoil and an NACA 65(1)-212 airfoil, both at an angle of attack of 4 degrees, were determined. The amount of water in droplet form impinging on the airfoils, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface affected were calculated from the trajectories and are presented. The amount, extent, and rate of impingement of the NACA 65(1)-208 airfoil are compared with the re… more
Date: May 1953
Creator: Brun, Rinaldo J.; Gallagher, Helen M. & Vogt, Dorothea E.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of the flow around lifting symmetrical double-wedge airfoils at Mach numbers of 1.30 and 1.41

Description: Report presenting measurements made of the flow around a 10-percent-thick, double symmetrical, two-dimensional wedge at Mach number 1.30 and a 14.2-percent-thick wedge at two Mach numbers for various angles of attack. Pressure and Mach number distributions, lift and drag coefficients, center of lift, and pitching moment are presented.
Date: March 1956
Creator: Gooderum, Paul B. & Wood, George P.
Partner: UNT Libraries Government Documents Department
open access

Tabulation of Mass-Flow Parameters for Use in Design of Turbomachine Blade Rows for Ratios of Specific Heats of 1.3 and 1.4

Description: Report presenting mass-flow tables for ratios of specific heats for the entire range of critical velocity ratio. The tables enable a quick and accurate determination of the integrated average specific mass flow across a region where the end-point velocities are known. A numerical example using the tables is also provided.
Date: October 1956
Creator: Whitney, Warren J.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and with several inlet boundary layers

Description: Report presenting an experimental investigation in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1, a 19-by-19-inch inlet, and five inlet boundary layers varying in thickness and shape parameter. Tests were performed over a range of Mach and Reynolds numbers. Results regarding velocity distribution, performance, and some general considerations for this configuration are provided.
Date: April 1952
Creator: Friedman, Daniel & Westphal, Willard R.
Partner: UNT Libraries Government Documents Department
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