National Advisory Committee for Aeronautics (NACA) - 30 Matching Results

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Aerodynamics of the Fuselage

Description: "The present report deals with a number of problems, particularly with the interaction of the fuselage with the wing and tail, on the basis of simple calculating method's derived from greatly idealized concepts. For the fuselage alone it affords, in variance with potential theory, a certain frictional lift in yawed flow, which, similar to the lift of a wing of small aspect ratio, is no longer linearly related to the angle of attack. Nevertheless there exists for this frictional lift something l… more
Date: December 1942
Creator: Multhopp, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of the effect of core structure and performance on volume and shape of cross-flow tubular intercoolers

Description: From Introduction: "The purpose of this paper is to show, in a similar manner, the effect of change in the core structure of the tubular intercooler on the over-all dimensions when the operating conditions are fixed."
Date: December 1942
Creator: Reuter, J. George & Valerino, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of beveled-trailing-edge elevators on a typical pursuit fuselage at altitudes simulating-normal flight and spin conditions

Description: Report presenting lift and elevator hinge-moment characteristics were measured on horizontal tail provided with elevators having three different beveled trailing edges. Results regarding fuselage alone and fuselage interference, lift characteristics of fuselage-tail combination, elevator hinge-moment characteristics, drag, and comparison with data from two-dimensional-flow tests are provided.
Date: December 1942
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Curing of Resin-Wood Combinations by High-Frequency Heating

Description: Note presenting a summary of the results of an investigation of the curing of resin-wood combinations by high-frequency heating. The physical facts pertinent to high-frequency heating are introduced and the procedure is described for measuring dielectric constant and loss from 1 to 100 megacycles. The results indicated that the high-frequency heating process is feasible, flexible, and timesaving.
Date: December 1942
Creator: von Hippel, Arthur R. & Dietz, A. G. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of airplane design efficiency and engine economy on range

Description: Report presenting an examination of the effects of variations in efficiency parameters, including engine economy, aerodynamic efficiency, and structural efficiency, on airplane performance. Efficiency parameters were found to be extremely ineffective in adjusting the airplane performance to its tactical mission as compared to primary parameters like altitude, power, gross weight, and wing area.
Date: December 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Changes in Aspect Ratio, Side Area, Flight-Path Angle, and Normal Acceleration on Lateral Stability

Description: Report presenting computations made to determine the effect of changes in wing aspect ratio, additional side area, flight-path angle, and normal acceleration on the relation between the fin area and the dihedral angle required for spiral and for oscillatory lateral stability for a hypothetical airplane of the pursuit or fighter categories. The diagrams indicate that the effect of wing aspect ratio on lateral stability is small.
Date: December 1942
Creator: Bamber, M. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Solidity, Blade Section, and Contravane Angle on the Characteristics of an Axial-Flow Fan

Description: Report presenting an axial flow fan tested with 5, 9, 12, 18, and 24 blades and with two different blade sections. The range of contravane angle and blade angle without contravanes was extended past results published for the same fan previously.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Various Surface Conditions on Press Fits of Steel Bushings and 17S-T Aluminum-Alloy Fittings

Description: Report presenting testing of specimens of 17S-T aluminum-alloy fittings with pressed-in steel bushings for various surface conditions. The surface conditions tested included bare surfaces, aonidcal coating and steel cadmium-plate, and one surface treated and the other bare, both without lubrication and with Gredag No. 83 as a lubricant. The calculated coefficients of friction for the various press fits for the investigation ranged from 0.33 for the unlubricated contact of bare steel and aluminu… more
Date: December 1942
Creator: Hartmann, E. C. & Reedy, J. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Exploration of the Longitudinal Tensile and Compressive Properties Throughout an Extruded Shape of 24S-T Aluminum Alloy

Description: Note presenting an investigation of tensile and compressive properties of specimens cut from an extruded shape of 24S-T aluminum alloy. The tensile strengths, tensile yield strengths, elongations, and compressive yield strengths of both the uncrystallized and recrystallized portions were determined. The strength of a cross section of an extruded shape is the weighted average of the strengths of the unrecrystallized and the recrystallized areas.
Date: December 1942
Creator: Paul, D. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight tests of NACA jet-propulsion exhaust stacks on the supermarine spitfire airplane

Description: Report presenting an investigation of the Supermarine Spitfire airplane equipped with exhaust stacks designed according to the jet-propulsion exhaust-stack system developed by the NACA. An increase in the high speed of the airplane of 6 mph was obtained as compared with the airplane equipped with the Rolls Royce exhaust system. Results regarding performance and exhaust-flame visibility are provided.
Date: December 1942
Creator: Turner, L. Richard & White, Maurice D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Generalized Selection Charts for Harrison and Tubular Intercoolers

Description: Report presenting a generalized selection chart for tubular cross-flow intercoolers and another chart for Harrison cross-flow intercoolers. The charts make it easier to select intercoolers for any particular set of design conditions and under limitations on dimensions and pressure drops.
Date: December 1942
Creator: Wood, George P. & Tifford, Arthur N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of a 1/6-Scale Model of a Twin-Engine Pursuit Airplane

Description: Report presenting testing of a scale model of a twin-engine pursuit airplane in order to investigate the possibility of high-speed diving difficulties and to find remedies for them. Most of the data were obtained in force tests, although some pressure-distribution measurements, elevator hinge moments, and wake surveys were also made. The tests showed that the airplane will experience serious diving moments above lift coefficients of 0.5 at a Mach number of 0.65, and 0.1 at a Mach number of 0.72… more
Date: December 1942
Creator: Ganzer, Victor M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 5: Theory and Use of Heat Meters for the Measurement of Rates of Heat Transfer Which Are Independent of Time

Description: Report presenting a description of a meter which will measure the heat flowing through surfaces. Its operation is based on the measurement of the temperature decrease through a fixed thermal resistance. Only the case of heat flow independent of time is discussed in this particular report.
Date: December 1942
Creator: Martinelli, R. C.; Morrin, E. H. & Boelter, L. M. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 6: Heat Transfer Equations for the Single Pass Longitudinal Exchanger

Description: Report presenting an analysis of parallel flow and contraflow single pass heat exchangers, together with charts which allow the direct evaluation of the thermal performance of the units without recourse to trail-and-error techniques. The use of equations and charts is illustrated by several examples.
Date: December 1942
Creator: Martinelli, R. C.; Morrin, E. H. & Boelter, L. M. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Limiting Useful Deflections of Corrugated Metal Diaphragms

Description: Note presenting measurements made on a large number of corrugated diaphragms of similar shapes but of various sizes and various metals. Some of the materials studied include phosphor bronze, beryllium copper, A-Nickel, B-Monel, K-Monel, and Inconel. Results regarding pressure deflection, hysteresis, drift, aftereffect, recovery, and zero shift, and design and selection of diaphragms are provided.
Date: December 1942
Creator: Wildhack, W. A. & Goerke, V. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for calculating heat transfer in the laminar flow region of bodies

Description: Report presenting a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited to use to the determination of heat transfer fro the forward section of such bodies when the flow is laminar.
Date: December 1942
Creator: Allen, H. Julian & Look, Bonne C.
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: From Summary: "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, for example."
Date: December 1942
Creator: Frick, Charles W., Jr. & McCullough, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method of Calculating Bending Stresses Due to Torsion

Description: Report presenting a method for analyzing bending stresses due to torsion in a box with variable cross section and loading by means of a recurrence formula leading to a set of equations identical in form with the well-known three-moment equations. An approximate form of the general method of analysis is presented that eliminates the need of solving a system of equations.
Date: December 1942
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Performance of a Vaneless Diffuser Fan

Description: "The present paper is devoted to the theoretical and experimental investigation of one of the stationary elements of a fan, namely, the vaneless diffuser. The method of computation is based on the principles developed by Pfleiderer (Forschungsarbeiten No. 295). The practical interest of this investigation arises from the fact that the design of the fan guide elements - vaneless diffusers, guide vanes, spiral casing - is far behind the design of the impeller as regards accuracy and reliability" … more
Date: December 1942
Creator: Polikovsky, V. & Nevelson, M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Investigation of the Characteristics of Air Scoops on a Fuselage

Description: Report presenting an investigation of the characteristics of air scoops in the NACA propeller-research tunnel. The investigation showed that, at inlet-velocity ratios equal to or greater than 0.3, scoops in a forward position on the fuselage gave total pressures in the inlet nearly equal to free-stream total pressure.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Rosette Strain Computer

Description: Note presenting a description of an electrical apparatus that serves as a computer for the evaluation of linear strain measurements taken in rosette fashion on the surface of a structural element carrying tension or compression and shear. The solution of the strain circle is accomplished by coupled rotary transformers, one representing each of the rosette gages.
Date: December 1942
Creator: Klemperer, W. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Strength and Stiffness of Shear Webs With Round Lightening Holes Having 45 Degree Flanges

Description: Report presenting tests made of 18 shear webs with round lightening holes having 45 degree flanges. the purpose of the tests was to extend the range of a previous investigation to larger ratios of hole diameter to web depth and of web depth to web thickness. Simple empirical formulas are given for the strength and the stiffness of shear webs.
Date: December 1942
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Strength Tests of Thin-Wall Truncated Cones of Circular Section

Description: "The ends of thin-wall truncated cones of circular section were clamped to rigid bulkheads and the cones subjected to strength tests. The results from torsion tests of five, compression tests of three, and tests in combined transverse shear and bending of 18 truncated cones are given herein. The results of the tests are correlated with the previously published results of corresponding tests of circular cylinders and are presented in charts suitable for use in design" (p. 1).
Date: December 1942
Creator: Lundquist, Eugene E. & Schuette, Evan H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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