National Advisory Committee for Aeronautics (NACA) - 425 Matching Results

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An Analysis of the Dissipation of Heat in Conditions of Icing From a Section of the Wing of the C-46 Airplane

Description: From Introduction: "The performance of the heated wing of the C-46 airplane (reference 1), in conditions of icing, has been analyzed. The method of calculating the dissipation of heat, both by convection and by evaporation, from a heated surface exposed to conditions of icing is given in reference 2."
Date: 1945%
Creator: Hardy, J. K.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculations of Economy of 18-Cylinder Radial Aircraft Engine With Exhaust-Gas Turbine Geared to the Crankshaft

Description: Calculations based on dynamometer test-stand data obtained on an 18-cylinder radial engine were made to determine the improvement in fuel consumption that can be obtained at various altitudes by gearing an exhaust-gas turbine to the engine crankshaft in order to increase the engine-shaft work.
Date: January 1, 1945
Creator: Hannum, Richard W. & Zimmerman, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts of Pressure, Density, and Temperature Changes at an Abrupt Increase in Cross-Sectional Area of Flow of Compressible Air

Description: "Equations have been derived for the change in the quantities that define the thermodynamic state of air - pressure, density, and temperature - at an abrupt increase in cross-sectional area of flow of compressible air. Results calculated from these equations are given in a table and are plotted as curves showing the variation of the calculated qualities with the area expansion ratio in terms of the initial Mach number as parameter. Only the subsonic region of flow is considered" (p. 1).
Date: January 1945
Creator: Joyner, Upshur T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of Engine-Cooling Data

Description: Report discusses a method of correlating engine-cooling data and its application to a representative engine-cooling test. Considerations for the correlation method are given, but the application to specific engine-cooling problems should be simple and direct. Information about experimental procedure and an example with specific values are included.
Date: January 1945
Creator: Brimley, D. E. & Brevoort, Maurice J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of Wright Aeronautical Corporation Cooling Data on the R-3350-14 Intermediate Engine and Comparison With Data From the Langley 16-Foot High-Speed Tunnel

Description: Report presenting a comparison of the cooling-test data obtained on the identical Wright R-3350-14 engine equipped with the same cooling pressure-tube installation. The comparison reveals the large difference in cooling pressure drop that may be obtained in different test installations with the identical engine and pressure-tube installation because of an injudicious choice of pressure-tube locations.
Date: January 1945
Creator: Pinkel, Benjamin & Rubert, Kennedy F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical combinations of shear and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Description: Report presenting an exact solution and a closely concurring approximate energy solution for the buckling of an infinitely long flat plate under combined shear and transverse direct stress with edges elastically restrained against rotation. An appreciable fraction of the critical stress in pure shear may be applied to the plate without any reduction in the transverse compressive stress necessary to produce buckling.
Date: January 1945
Creator: Batdorf, S. B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ditching behavior of military airplanes as affected by ditching aids

Description: Report presenting an investigation of planing devices like hydroflaps and hydrofoils on several dynamically scaled models of military airplanes and their effectiveness in improving ditching characteristics. The ditching aids were generally found to be of value. Results regarding the hydroflap test in the impact basin, dynamic model tests at the outdoor catapult, and effect of ditching aids on ditching performance and rough water are provided.
Date: January 1945
Creator: Steiner, Margaret F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine 2: Blends of 2,2,3-Trimethylpentane with 28-R

Description: "The knock-limited performance of blends of 0,50; and 100 percent by volume of 2,2,3-trimethylpentane in 28-R fuel determined with a modified F-4 engine at three sets of conditions varying from severe to mild at each of three compression ratios (6.0, 8.0, and 10.0). A comparison of the knock-limited performance of 2,2,3-trimethylpentane with that of triptane (2,2,3-trimethylbutane) is included. The knock-Limited performance of 2,2,3-trimethylpontane was usually more sensitive to either compres… more
Date: January 1945
Creator: Alquist, Henry E. & Tower, Leonard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of high loading on landing technique and distance, with experimental data for the B-26 airplane

Description: Report presenting an analysis of the effect of wing loading of the landing flare, which indicated that it had an important effect on landing technique and distance. Results regarding the approach and flare path and ground run are provided.
Date: January 1945
Creator: O'Sullivan, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of trailing-edge extension flaps on propeller characteristics

Description: Report presenting an analysis to determine the effect on propeller performance of extension flaps added to the trailing edge of a propeller blade. A method is included to determine the angle that the flap extension must make with the chord in order to obtain a particular load distribution.
Date: January 1945
Creator: Crigler, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of compressibility on maximum lift coefficients for six propeller airfoils

Description: Report presenting an extension of previously reported data on the variation of maximum lift coefficient with Mach number, camber, and thickness ratio. The data were obtained from pressure-distribution tests in the 8-foot high-speed tunnel of six propeller airfoils of 1-foot chord.
Date: January 1945
Creator: Cleary, Harold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Elastic Constants for Wrought Aluminum Alloys

Description: "There are several constants which have been devised as numerical representations of the behavior of metals under the action of loadings which stress the metal within the range of elastic action. Some of these constants, such as Young's modulus of elasticity in tension and compression, shearing modulus of elasticity, and Poisson's ratio, are regularly used in engineering calculations. Precise tests and experience indicate that these elastic constants are practically unaffected by many of the fa… more
Date: January 1945
Creator: Templin, R. L. & Hartmann, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An empirical formula for the critical shear stress of curved sheets

Description: Report presenting tests to determine the critical shear stress of curved sheets. The empirical formula derived from the tests is applicable to panels with a ratio of radius to thickness of 300 or greater, a central angle of 1 radian or less, and a ratio of arc length to axial length not greater than 1.
Date: January 1945
Creator: Kuhn, Paul & Levin, L. Ross
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimation of F-3 and F-4 Knock-Limited Performance Ratings for Ternary and Quaternary Blends Containing Triptane or Other High-Antiknock Aviation-Fuel Blending Agents

Description: Report providing charts to assist with estimating F-3 and F-4 knock-limited performance ratings for several ternary and quaternary fuel blends. Several unusual behaviors were noted in the F-3 engines using the aromatic-paraffinic blends, so the charts for them may not be as accurate. General trends observed in different types of fuel are also described.
Date: January 1945
Creator: Barnett, Henry C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails

Description: Report presenting an analysis of available data on vee-tail surfaces. The analysis indicated that a vee tail designed to provide values of stability and control parameters equal to those provided by a conventional tail would probably provide no reduction in area unless the conventional vertical tail is in a bad canopy wake or unless the vee tail has a higher effective aspect ratio than the conventional vertical and horizontal tails.
Date: January 1945
Creator: Purser, Paul E. & Campbell, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Force and Moment Coefficients for a Thin Airfoil With Flap and Tab in a Form Useful for Stability and Control Calculations

Description: Note presenting the necessary pressure and force coefficients acting on a thin airfoil with a flap and tab in a form suitable for stability calculations in order to design improved control arrangements.
Date: January 1945
Creator: White, Roland J. & Klampe, Dean G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Friction in Pipes at Supersonic and Subsonic Velocities

Description: Note presenting an experimental determination of the apparent friction coefficient for the flow of air through smooth pipes at subsonic and supersonic velocities. In supersonic flow, the results were found to be strongly influenced by the presence of oblique shocks formed at the junction of nozzle and pipe. Results regarding the apparent friction coefficient, subsonic flow, supersonic flow, and comparisons with other investigations are provided.
Date: January 1945
Creator: Keenan, Joseph H. & Neumann, Ernest P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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General theory of airfoil sections having arbitrary shape or pressure distribution

Description: In this report a theory of thin airfoils of small camber is developed which permits either the velocity distribution corresponding to a given airfoil shape, or the airfoil shape corresponding to a given velocity distribution to be calculated. The procedures to be employed in these calculations are outlined and illustrated with suitable examples.
Date: 1945
Creator: Allen, H. Julian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Backflow Phenomenon in Centrifugal Compressors

Description: Report presents the results of an investigation conducted to determine the nature and the extent of the reversal of flow, which occurs at the inlet of centrifugal compressors over a considerable portion of the operating range. Qualitative studies of this flow reversal were made by lampblack patterns taken on a mixed-flow-type impeller and by tuft studies made on a conventional centrifugal compressor. Quantitative studies were made on a compressor specially designed to enable survey of angularit… more
Date: 1945
Creator: Benser, William A. & Moses, Jason J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The knock-limited performance of fuel blends containing aromatics 2: isopropylbenzene, benzene, and o-xylene

Description: Report presenting knock-limited small-scale-engine tests of isopropyl-benzene, benzene, and o-xylene blended individually in various concentrations with selected base fuels. Data were obtained to determine the blending sensitivity, lead susceptibility, and sensitivity of the blends to inlet-air temperatures. Isopropylbenzene was found to be the most effective overall.
Date: January 1945
Creator: Branstetter, J. Robert & Meyer, Carl L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for determining the rate of heat transfer from a wing or streamline body

Description: A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude. To illustrate the method, the total rate of heat transfer from an airfoil is calculated and co… more
Date: 1945
Creator: Frick, Charles W. & McCullough, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Principles of Moment Distribution Applied to Stability of Structures Composed of Bars or Plates

Description: "The principles of the cross method of moment distribution, which have previously been applied to the stability of structures composed of bars under axial load, are applied to the stability of structures composed of long plates under longitudinal load. A brief theoretical treatment of the subject, as applied to structures composed of either bars or plates, is included, together with an illustrative example for each of these two types of structure. An appendix presents the derivation of the form… more
Date: 1945
Creator: Lundquist, Eugene E.; Stowell, Elbridge Z. & Schuette, Evan H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Shear Elastic Properties of Some High Strength Nonferrous Metals as Affected by Plastic Deformation and by Heat Treatment

Description: Note presenting a study of the shear elastic properties of monel, nickel, Inconel, and aluminum-model tubing, as influenced by extension of annealed specimens, by cold reduction during manufacture, and by stress-relief annealing of cold-reduced materials. With slight extension of annealed tubing, the shear proof stresses generally decrease, owing to induced internal stress.
Date: January 1945
Creator: Mebs, R. W. & McAdam, D. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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