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  • Other Sources  (1,581)
  • 1940-1944  (1,581)
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Source
Keywords
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Year
  • 101
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    Beziehungen von Klima und Witterung zur Häufigkeit der Pflanzenkrankheiten in Schleswig-Holstein (1940)
    In:  Kühn-Archiv 54; p.403-430
    Details
    Publication Date: 1940
    Description: Der Autor gibt die wichtigsten Schaderreger an Kulturpflanzen in Schleswig-Holstein an und begründet ihr mittleres Vorkommen mit den klimatischen Gegebenheiten der Region. Des Weiteren werden die Witterungsbedingungen der Jahre 1936-1938 genutzt, um die tatsächliche Häufigkeit des Auftretens der genannten Schaderreger zu erklären. In einem weiteren Abschnitt wird das regional unterschiedliche Auftreten von Schadorganismen mit den regionalen klimatischen Unterschieden in Schleswig-Holstein zu erklären versucht. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Schleswig-Holstein ; 1925-1938
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    BIBLIOGRAPHY INKA BB
  • 102
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    Ein Verfahren zur statistischen Untersuchung der Abhängigkeit der Ernteerträge von Standort und klimatischen Faktoren. Forschungsdienst 13:301. (1942)
    In:  Forschungsdienst 13:301.
    Details
    Publication Date: 1942
    Description: Betrachtung des Klimas (Temperatur und Niederschlag) in Dekaden und Bildung von Ertrags-, Temperatur- und Niederschlagsklassen und daraus Ableitungen über die Beziehungen Ertrag und Witterung KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag) auf den Ertrag KATASTER-DETAIL: Delta T (März) + und Delta Nied (März) +, dann Erträge +; Delta T (April -, dann Erträge +; Delta Nied (Ende Juni,Ende Juli)-, dann Erträge + Delta T (Anfang Juli) +, dann Erträge +
    Keywords: Schlesien ; 1926-38 ; Boden ; Ertrag ; Niederschlag ; Weizen ; Witterung
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    BIBLIOGRAPHY INKA BB
  • 103
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    Eine Darstellung der ursächlichen Wechselbeziehungen zwischen Witterungsverlauf und Bodenzustand in ihren Auswirkungen auf Pflanzenwuchs und Ernte (1942)
    In:  Klima / Boden / Ernte Verlag C.V. Engelhard, Berlin. p. 7, 114-127
    Details
    Publication Date: 1942
    Description: Beziehung zwischen Witterungsablauf und Bodenzustand und deren Auswirkung auf Pflanzenwuchs und Ernte KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag von Kartoffeln KATASTER-DETAIL: Delta T (April bis Juli) -, dann Erträge (Kartoffel) +; Delta Nied (April bis Juli) -, dann Erträge (Kartoffel) -
    Keywords: Gesamtpreußen, Deutschland,Schlesien ; 1921-1932,1934 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Hafer ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung ; Hackfrüchte
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    BIBLIOGRAPHY INKA BB
  • 104
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    Beziehung zwischen Klimafaktoren und Getreideerträgen auf Standorten der mittelschlesischen Ackerebene (1940)
    In:  Diss. Breslau
    Details
    Publication Date: 1940
    Keywords: Schlesien
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    BIBLIOGRAPHY INKA BB
  • 105
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    Seismicity of the earth (1941)
    Geol. Soc. Am.
    In:  New York, 7 + 131 pp., Geol. Soc. Am., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Seismicity ; Review article
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    BIBLIOGRAPHY SEISMOLOGY
  • 106
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    A Treatise on the Mathematical Theory of Elasticity (1944)
    Dover Publ.
    In:  New York, Dover Publ., vol. 5, no. 22, pp. 662-664, (ISBN 0-470-87000-1 (HB), ISBN 0-470-87001-X (PB))
    Details
    Publication Date: 1944
    Keywords: Textbook of geophysics ; Elasticity ; Dislocation
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    BIBLIOGRAPHY SEISMOLOGY
  • 107
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    Deep focus earthquakes in America (1940)
    University of California Press
    In:  Pacific Science Association, 6th Congress Proceedings, vol. 1, Toronto, University of California Press, vol. 10, no. GL-TR-89-0230, pp. 149-150, (ISBN 3-933346-037)
    Details
    Publication Date: 1940
    Keywords: Seismology ; Seismicity ; Hypocentral depth
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    BIBLIOGRAPHY SEISMOLOGY
  • 108
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    A contribution to the seismic history of Missouri (1941)
    In:  Bull. Seism. Soc. Am., Oxford and Edinburgh, Blackwell Scientific Publications, vol. 31, no. 19, pp. 187-224, pp. 1484, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Seismicity ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 109
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    Seismicity of Central and South America (1942)
    In:  8th American Science Congress Washington 1940, Proceedings, vol. 4, Toronto, University of California Press, vol. 10, no. GL-TR-89-0230, pp. 455, (ISBN 3-933346-037)
    Details
    Publication Date: 1942
    Keywords: Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 110
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    Spectrographic observations of peculiar stars. iii (1942)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Keywords: unknown
    Format: text
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    NASA TECHNICAL REPORTS
  • 111
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    KEEPING AMERICA FIRST IN THE AIR (1944)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Keywords: BIOSCIENCES
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  • 112
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    Summary of investigations undertaken at langley memorial aeronautical laboratory on problem of aircraft icing (1941)
    In:  Other Sources
    Details
    Publication Date: 2011-08-10
    Keywords: unknown
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    NASA TECHNICAL REPORTS
  • 113
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    The Development of a New Lateral-Control Arrangement (1941)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Development work on an arrangement using ailerons and spoilers for lateral control was carried out by the Vought-Sikorsky Aircraft Division of the United Aircraft Corporation on a small commercial airplane in flight and on an airfoil in a wind tunnel. Spoiler hinge moments were reduced by aerodynamic balance. The arrangement was then built into an experimental airplane and further improvements were adopted as the result of flight and tunnel tests. The use of ailerons for lateral control with flaps up, spoilers with flaps full down, and gradual transition as the flaps are lowered was found to provide lateral control under the flight conditions for which they were best suited. The ailerons were of short span, permitting the use of long-span flaps, and were drooped to a relatively large angle when the flaps were deflected. A high maximum lift coefficient was thus attained. With large control deflections in the intermediate flap-angle range and spoiler effectiveness near neutral improved by "ventilating" the spoiler, the lateral control was satisfactory for the experimental airplane and was a definite improvement over that of a conventional control arrangement.
    Keywords: Aircraft Design, Testing and Performance
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  • 114
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    Preliminary Results of Flight Tests of a Conventional Three-Blade Propeller at High Speeds (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: As part of the program of flight tests of airplane propellers to determine compressibility effects at high speeds, preliminary flights have been made with a conventional three-blade propeller (Hamilton Standard 3155-6) on a Bell YP-39 airplane. This preliminary report presents the high-speed data obtained thus far with a brief analysis of the results.
    Keywords: Aerodynamics
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  • 115
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    Antispin-Tail-Parachute Installations (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Although antispin tail parachutes have been used successfully in spin demonstrations for some time, very little published information is available concerning the size of parachute, the bridle-line length, and the type and location of pack to use for particular airplane. The present paper is an attempt to supply data relating to these factors. The paper is in two parts. The first part reviews the principles of operation of the antispin parachutes, views the principles of operation of the antispin parachutes, summarized available information on actual installations, and discusses parachute loads and pack locations. The second part of the paper reports on systematic tests in the NACA-15-foot and 20-foot free-spinning tunnels at the Langley memorial Aeronautical Laboratory to determine the minimum size and the optimum bridle-line lengths for antispin tail parachutes for current military airplanes. It is concluded that airplanes weighing between 7500 and 14,000 pounds require parachutes 8 feet in diameter and bridle-line lengths between 20 and 50 feet. A positive-ejection mechanism is desirable to throw the parachute clear of the tail and to assure rapid opening. The pack and attachment point must be so located that the equipment will not foul the tail surfaces.
    Keywords: Aircraft Stability and Control
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  • 116
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    Tests of the XP-46 Airplane in the N.A.C.A. Full-Scale Wind Tunnel (1940)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: An investigation has been conducted on a full-scale model of the proposed XP-46 airplane in the N. A. C. A. full-scale wind tunnel pursuant to the request of the Amy Air Corps, Materiel Division. The primary purpose of the investigation was to determine the optimum arrangement of the various component parts to obtain the maximum high speed and to provide adequate engine cooling. Additional tests included a determination of the stalling characteristics and the effectiveness of ailerons and elevators. The profile drag of the wing was ascertained by the momentum method; the location of the transition point on the wing and the critical compressibility velocities of the various airplane components were determined from surface pressure surveys.
    Keywords: Aircraft Design, Testing and Performance
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  • 117
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    Flight Tests of Internally Balanced, Sealed Ailerons on the Curtiss XP-60 Airplane (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Results are presented of brief flight tests of the aileron characteristics of the XP-60 airplane with internally balanced, sealed ailerons, which were developed by the NACA for use, particularly, on low-drag-type wings. The results show that light and effective aileron control was obtained without evidence of overbalance or undesirable shaking of the control system at any part of the deflection range within the level-flight speed range.
    Keywords: Aircraft Design, Testing and Performance; Aircraft Stability and Control
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  • 118
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    A Theoretical Investigation of Longitudinal Stability of Airplanes with Free Controls Including Effect of Friction in Control System (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The relation between the elevator hinge moment parameters and the control forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance. The stability of the short period oscillations is shown as a series of boundaries giving the limits of the stable regions in terms of the elevator hinge moment parameters. The effects of static stability, elevator moment of inertia, elevator mass unbalance, and airplane density are also considered. Dynamic instability is likely to occur if there is mass unbalance of the elevator control system combined with a small restoring tendency (high aerodynamic balance). This instability can be prevented by a rearrangement of the unbalancing weights which, however, involves an increase of the amount of weight necessary. It can also be prevented by the addition of viscous friction to the elevator control system provided the airplane center of gravity is not behind a certain critical position. For high values of the density parameter, which correspond to high altitudes of flight, the addition of moderate amounts of viscous friction may be destabilizing even when the airplane is statically stable. In this case, increasing the viscous friction makes the oscillation stable again. The condition in which viscous friction causes dynamic instability of a statically stable airplane is limited to a definite range of hinge moment parameters. It is shown that, when viscous friction causes increasing oscillations, solid friction will produce steady oscillations having an amplitude proportional to the amount of friction.
    Keywords: Aircraft Stability and Control
    Type: AD-A301267 , NACA-TR-791
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  • 119
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    A Method of Estimating the Knock Rating of Hydrocarbon Fuel Blends (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends.
    Keywords: Propellants and Fuels
    Type: AD-A301347 , NACA-TR-760 , NASA-TM-111362 , NAS 1.15:111362
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    NASA TECHNICAL REPORTS
  • 120
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    Control-Surface Instability on High-Speed Airplanes (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Tests of several modern airplanes indicate that control surfaces with a high degree of aerodynamic balance are likely to possess characteristics which make them unsatisfactory or dangerous in high-speed flight. Dive tests made in the spring of 1940 at the NACA on a naval fighter-type airplane illustrate one form of instability that may be encountered. During a dive at an indicated airspeed of 365 miles per hour, the ailerons suddenly overbalanced. The efforts of the pilot to bring the ailerons back to neutral resulted in a violent oscillation of the control stick from side to side. Fortunately, the force required to return the ailerons to neutral was within the pilot's capabilities. A time history of the maneuver is given in figure1 and typical frames from motion pictures of the cockpit and of the wing, taken during the maneuver, are given in figure 2. In the illustrated case, the occurrence of aerodynamic overbalance was attributed to a slight bulge, approximately 1/16 inch thick, on the lower surface of the leading edges of the ailerons, caused by the installation of additional mass balance ahead of the hinge line. A drawing showing the shape of the bulge is given in figure 3. After this slight protuberance had been eliminated, dives were successfully made at higher speeds.
    Keywords: Aircraft Stability and Control
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    NASA TECHNICAL REPORTS
  • 121
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    New Research on the Cowling and Cooling of Radial Engines (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: An extensive series of wind-tunnel tests on a half-scale conventional, nacelle model were made by the United Aircraft Corporation to determine and correlate the effects of many variables on cooling air flow and nacelle drag. The primary investigation was concerned with the reaction of these factors to varying conditions ahead of, across, and behind the engine. In the light of this investigation, common misconceptions and factors which are frequently overlooked in the cooling and cowling of radial engines are considered in some detail. Data are presented to support certain design recommendations and conclusions which should lead toward the improvement of present engine installations. Several charts are included to facilitate the estimation of cooling drag, available cooling pressure, and cowl exit area.
    Keywords: Aircraft Design, Testing and Performance
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    NASA TECHNICAL REPORTS
  • 122
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    NACA Apparatus and Methods for Take-Off and Landing Measurements (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Experience has shown that the determination of the take-off and. landing characteristics of airplanes requires specialized, equipment of a high degree of precision and reliability and demands great care in the evaluation and interpretation of data. It is believed, therefore, that a description of the apparatus and methods that have been developed by the NACA for these measurements might be of considerable interest, particularly to flight-test groups that have had little experience with landing and. take-off measurements. The basic principles and essential details of the Committee's equipment are described, the methods of utilizing the apparatus and of reducing the data are explained, and sample test results are presented.
    Keywords: Aircraft Design, Testing and Performance
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  • 123
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    An Investigation of the Validity of Wang's Formula for the Critical Load for Circular Cylindrical Grids (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Four circular cylindrical grids were tested under axial compression to investigate the validity of a theoretical formula for the critical load for such structures. The chief result of the investigation was to throw light on some difficulties connected with the experimental validation of such formulas.
    Keywords: Theoretical Mathematics; Structural Mechanics
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  • 124
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    A Study of the Compressive Strength of Stiffened Plywood Panels (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: The results of compression tests on 44 stiffened plywood panels are presented and correlated in groups for the three types of failure observed: column failure, failure by separation of plywood from stiffener, and crushing failure. The expanded program of military aircraft construction has made it necessary to seek substitute materials that can be used in aircraft in place of aluminum alloys. Wood is one of these substitute materials. The development of synthetic resins as bonding and impregnating agents has resulted in the production of plywood which is being used in stressed-skin structures for aircraft. The use of plywood in such structures necessitates that tests be performed. to determine allowable stress values for use in design, This report presents a preliminary analysis of the results of compression tests on 44 stiffened plywood panels made by the Universal Moulded Products Corporation. The tests were made in a testing machine of 1,200,000 pounds capacity in the NACA structures research laboratory.
    Keywords: Aircraft Design, Testing and Performance; Structural Mechanics
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    NASA TECHNICAL REPORTS
  • 125
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    Effect of Fabric Deflection on Control Characteristics (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: In the past fabric-covered control surfaces have been widely used on airplanes without noticeable averse effects. On modern high-speed airplanes, however, several instances have been observed in which undesirable control force characteristics were attributed to deflection of the fabric on the control surfaces.
    Keywords: Aircraft Design, Testing and Performance; Nonmetallic Materials; Aircraft Stability and Control
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    NASA TECHNICAL REPORTS
  • 126
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    Model tests of a wing-duct system for auxiliary air supply (1941)
    In:  CASI
    Details
    Publication Date: 2019-05-31
    Keywords: unknown
    Type: NASA-TM-X-57675 , NACA-SR-175
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  • 127
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    Low-speed flight investigation of an airplane with sweptback wings (1943)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 145-152
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  • 128
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    Preliminary Investigation Directed Toward Improvement of the NACA Cowling (1942)
    In:  CASI
    Details
    Publication Date: 2018-08-03
    Description: The development of new cowlings, applicable to a short-nose radial engine, is described. These cowlings, designated the NACA cowlings D(sub s) and D(sub sf), employ a larger spinner and a higher inlet-velocity ratio than does the conventional NACA cowling C. The pressures available for cooling and the estimated critical Mach number were found to be higher with the new cowlings than are usually encountered with the conventional NACA cowling C. Large-chord propeller cuffs were found to have a stabilizing effect on the flow entering the cowling and resulted in increased front pressures. Fan blades mounted on the spinner in the inlet opening had a similar effect.
    Keywords: Aircraft Propulsion and Power
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  • 129
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    Experimental investigation of a new type of low-drag wing-nacelle combination (1942)
    In:  CASI
    Details
    Publication Date: 2019-05-31
    Keywords: unknown
    Type: NACA-SR-229
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  • 130
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    Simply supported long rectangular plate under combined axial load and normal pressure (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-949
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  • 131
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    Stresses at Cut-outs in Shear Resistant Webs as Determined by the Photoelastic Method (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-984
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  • 132
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    Guides for preventing buckling in axial fatigue tests of thin sheet-metal specimens (1944)
    In:  CASI
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    Publication Date: 2019-06-28
    Type: NACA-TN-931
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  • 133
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    Wind-tunnel Investigation of the Effect of Vertical Position of the Wing on the Side Flow in the Region of the Vertical Tail (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-804
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  • 134
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    Normal pressure tests on unstiffened flat plates (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flat sheet panels of aluminum alloy (all 17S-T except for two specimens of 24S-T) were tested under normal pressures with clamped edge supports in the structures laboratory of the Guggenheim Aeronautical Laboratory, California Institute of Technology. The thicknesses used ranged from 0.010 to 0.080 inch; the panel sizes ranged from 10 by 10 inches to 10 by 40 inches; and the pressure range was from 0 to 60-pounds-per-square-inch gage. Deflection patterns were measured and maximum tensile strains in the center of the panel were determined by electric strain gages. The experimental data are presented by pressure-strain, pressure-maximum-deflection, and pressure-deflection curves. The results of these tests have been compared with the corresponding strains and deflections as calculated by the simple membrane theory and by large deflection theories.
    Type: NACA-TN-943
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  • 135
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    The numerical solution of compressible fluid flow problems (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Numerical methods have been developed for obtaining the steady, adiabatic flow field of a frictionless, perfect gas about arbitrary two-dimensional bodies. The solutions include the subsonic velocity regions, the supersonic velocity regions, and the transition compression shocks, if required. Furthermore, the rotational motion and entropy changes following shocks are taken into account. Extensive use is made of the relaxation method. In this report the details of the methods of solution are emphasized so as to permit others to solve similar problems. Solutions already obtained are mentioned only by way of illustrating the possibilities of the methods described. The methods can be applied directly to wind tunnel and free air tests of arbitrary airfoil shapes at subsonic, sonic, and supersonic speeds.
    Type: NACA-TN-932
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  • 136
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    The inward bulge type buckling of monocoque cylinders I : calculation of the effect upon the buckling stress of a compressive force, a nonlinear direct stress distribution, and a shear force (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the present part I of a series of reports on the inward bulge type buckling of monocoque cylinders the buckling load in combined bending and compression is first derived. Next the reduction in the buckling load because of a nonlinear direct stress distribution is determined. In experiments nonlinearity may result from an inadequate stiffness of the end attachments in actual airplanes from the existence of concentrated loads or cut-outs. The effect of a shearing force upon the critical load is investigated through an analysis of the results of tests carried out at GALCIT with 55 reinforced monocoque cylinders. Finally, a simple criterion of general instability is presented in the form of a buckling inequality which should be helpful to the designer of a monocoque in determining the sizes of the rings required for excluding the possibility of inward bulge type buckling.
    Type: NACA-TN-938
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  • 137
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    Torsion Test of a Monocoque Box (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A monocoque box beam consisting of a 24S-T aluminum-alloy sheet reinforced by four bulkheads and by longitudinal stringers and corner posts was subjected to bending loads as follows: pure bending about the lift axis, cantilever bending about the lift axis, and pure bending about both lift and drag axis. Longitudinal strains were measured for loads up to a load at which permanent set became measurable. The loads were sufficient to produce buckling of the sheet between stringers on the compression side of the box. The only noticeable effect of this buckling was a small increase in extreme-fiber strain on the compression side. The measured strains and measured deflections differed less than 10 percent from those computed from the simple beam theory after taking account of the effective width of the buckled sheet. The effect of the bulkheads on the distribution of stringer strain was negligible.
    Type: NACA-TN-873
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  • 138
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    Analysis of square shear web above buckling load (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A solution of Von Karman's fundamental equations for plates with large deflections is presented for the case of a shear web divided into square panels by reinforcing struts. Numerical solutions are given for struts of infinite rigidity and for struts the weight of which is one-fourth the weight of the sheet. The results are compared with Wagner's diagonal tension theory as extended by Kuhn and by Langhaar. It is found that the diagonal tension theory as developed by Kuhn agrees best with the present paper in the practical range when r=1/4. Kuhn's theory is in especially good agreement for the force in the strut when r=1/4.
    Type: NACA-TN-962
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  • 139
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    Some Investigations of the General Instability of Stiffened Metal Cylinders II : Preliminary Tests of Wire-braced Specimens and Theoretical Studies (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is the second of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The first five reports of this series cover investigations of the general instability problem under the loading conditions of pure bending and were prepared under the sponsorship of the Civil Aeronautics Administration. The succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics.
    Type: NACA-TN-906
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  • 140
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    The aerodynamics of a wind-tunnel fan (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The vortex blade-element theory modified to apply to an axial fan working in a duct is reviewed. Thrust and power coefficients for a fan are identified with the corresponding coefficients for airplane propellers. The relation of pressure produced by the fan to the blade-element coefficients is developed. The distribution of axial velocity of fluid through a fan is assumed to be controlled by the fan itself. The radial distribution of tangential velocity imported by the fan to fluid moving through the fan is shown to be independent of the axial-velocity distribution. A nondimensional coefficient, designated the rotation constant, is introduced. This constant is based solely upon design information. The use of the rotation constant in simplifying the design of a fan for a specific operating condition is demonstrated. Based on the use of the rotation constant, a graphical method is outlined by which the performance of a given fan in a given wind tunnel may be predicted and by which the distributions of axial velocity of the fluid through the fan under various operating conditions may be established.
    Type: NACA-TN-820
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  • 141
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    Wind-tunnel investigation of an NACA 23012 airfoil with several arrangements of slotted flaps with extended lips (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the effect of slot-lip location on the aerodynamic section characteristics of an NACA 23012 airfoil with a 30-percent-chord slotted flap. Tests were made with slot lips located at 90 and 100 percent of the airfoil chord and with two different flap shapes. The results are compared with a slotted flap previously developed by the National advisory Committee for Aeronautics with a slot lip located at 83 percent of the airfoil chord. The extension of the slot lip to the rear increased the section lift and pitching-moment coefficients. Comparisons made on a basis of pitching moment for a given tail length show that the Fowler type flap, lip extended to trailing edge of the airfoil, has the greatest section lift coefficient. For moderate tail lengths, 2 to 3 chord lengths, there was only a slight difference between the previously developed slotted flap and the slotted flap with slot lip extended to 90 percent of the airfoil chord. Of the three flaps tested, the Fowler flap had the lowest drag coefficient at high lift coefficients. The extension of the lower surface at the leading edge of the slot had a negligible effect on the profile drag of the airfoil-flap arrangement with the flap deflected when the lip terminated at 90 percent of the airfoil chord.
    Type: NACA-TN-808
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  • 142
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    Correction of the lifting-line theory for the effect of the chord (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is shown that a simple correction for the chord of a finite wing can be deduced from the three-dimensional potential flow around an elliptic plate. When this flow is compared with the flow around a section of an endless plate, it is found that the edge velocity is reduced by the factor 1/E, where E is the ratio of the semiperimeter to the span. Applying this correction to the circulation brings the theoretical lift into closer agreement with experiments.
    Type: NACA-TN-817
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  • 143
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    On the general theory of thin airfoils for nonuniform motion (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: General thin-airfoil theory for a compressible fluid is formulated as boundary problem for the velocity potential, without recourse to the theory of vortex motion. On the basis of this formulation the integral equation of lifting-surface theory for an incompressible fluid is derived with the chordwise component of the fluid velocity at the airfoil as the function to be determined. It is shown how by integration by parts this integral equation can be transformed into the Biot-Savart theorem. A clarification is gained regarding the use of principal value definitions for the integral which occur. The integral equation of lifting-surface theory is used a s the starting point for the establishment of a theory for the nonstationary airfoil which is a generalization of lifting-line theory for the stationary airfoil and which might be called "lifting-strip" theory. Explicit expressions are given for section lift and section moment in terms of the circulation function, which for any given wing deflection is to be determined from an integral equation which is of the type of the equation of lifting-line theory. The results obtained are for airfoils of uniform chord. They can be extended to tapered airfoils. One of the main uses of the results should be that they furnish a practical means for the analysis of the aerodynamic span effect in the problem of wing flutter. The range of applicability of "lifting-strip" theory is the same as that of lifting-line theory so that its results may be applied to airfoils with aspect ratios as low as three.
    Type: NACA-TN-946
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  • 144
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    The inward bulge type buckling of monocoque cylinders II : experimental investigation of the buckling in combined bending and compression (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is the second part of a series of reports on the inward bulge type buckling of monocoque cylinders. It presents the results of an experimental investigation of buckling in combined bending and compression. In the investigation it was found that the theory developed in part I of the present series predicts the buckling load in combined bending and compression with the same degree of accuracy as the older theory does in pure bending. In the realm covered by the experiments no systematic variation of the parameter N was observed. The analysis of the test results afforded a check on the theories of buckling of a curved panel. The agreement between experiment and theory was reasonably good. In addition, the effect of the end conditions upon the stress distribution under loads and upon initial stresses was investigated.
    Type: NACA-TN-939
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  • 145
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    The "limiting line" in mixed subsonic and supersonic flow of compressible fluids (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is well known that the vorticity for any fluid element is constant if the fluid is non-viscous and the change of state of the fluid is isentropic. When a solid body is placed in a uniform stream, the flow far ahead of the body is irrotational. Then if the flow is further assumed to be isentropic, the vorticity will be zero over the whole filed of flow. In other words, the flow is irrotational. For such flow over a solid body, it is shown by Theodorsen that the solid body experiences no resistance. If the fluid has a small viscosity, its effect will be limited in the boundary layer over the solid body and the body will have a drag due to the skin friction. This type of essentially isentropic irrotational flow is generally observed for a streamlined body placed in a uniform stream, if the velocity of the stream is kept below the so-called "critical speed." At the critical speed or rather at a certain value of the ratio of the velocity of the undisturbed flow and the corresponding velocity of sound, shock waves appear. This phenomenon is called the "compressibility bubble." Along a shock wave, the change of state of the fluid is no longer isentropic, although still adiabatic. This results in an increase in entropy of the fluid and generally introduces vorticity in an originally irrotational flow. The increase in entropy of the fluid is, of course, the consequence of changing part of the mechanical energy into heat energy. In other words, the part of fluid affected by the shock wave has a reduced mechanical energy. Therefore, with the appearance of shock waves, the wake of the streamline body is very much widened, and the drag increases drastically. Furthermore, the accompanying change in the pressure distribution over the body changes the aerodynamic moment acting on it and in the case of an airfoil decreases the lift force. All these consequences of the breakdown of isentropic irrotational flow are generally undesirable in applied aerodynamics. Its occurrence should be delayed as much as possible by modifying the shape or contour of the body. However, such endeavor will be very much facilitated if the cause or the criterion for the breakdown can be found first.
    Type: NACA-TN-961
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  • 146
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    Dynamics of the inlet system of a four-stroke engine (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were run on a single-cylinder and a multicylinder four-stroke engine in order to determine the effect of the dynamics of the inlet system upon indicated mean effective pressure. Tests on the single-cylinder engine were made at various speeds, inlet valve timings, and inlet pipe lengths. These tests indicated that the indicated mean effective pressure could be raised considerably at any one speed by the use of a suitably long inlet pipe. Tests at other speeds with this length of pipe showed higher indicated mean effective pressure than with a very short pipe, although not so high as could be obtained with the pipe length adjusted for each speed. A general relation was discovered between optimum time of inlet valve closing and pipe length; namely, that longer pipes require later inlet valve closing in order to be fully effective. Tests were also made on three cylinders connected to a single pipe. With this arrangement, increased volumetric efficiency at low speed was obtainable by using a long pipe, but only with a sacrifice of volumetric efficiency at high speed. Volumetric efficiency at high speed was progressively lower as the pipe length was increased.
    Type: NACA-TN-935
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  • 147
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    Axial Fatigue Tests at Zero Mean Stress of 24S-T Aluminum-alloy Sheet with and Without a Circular Hole (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Axial fatigue tests were made on 189 coupon specimens of 0.032-inch 24S-T aluminum-alloy sheet and a few supplementary specimens of 0.004-inch sheet. The mean load was zero. The specimens were restrained against lateral buckling by lubricated solid guides described in a previous report on this project. About two-thirds of the 0.032-inch specimens were plain coupons nominally free from stress raisers. The remainder contained a 0.1285-inch drilled hole at the center where the reduced section was 0.5 inch wide. S-N diagrams were obtained for cycles to failure between about 1000 and 10 to the 7th power cycles for the plain specimens and 17 and 10 to the 7th power cycles for the drilled specimens. The fatigue stress concentration factor increased from about 1.08 for a stress amplitude causing failure at 0.25 cycles (static) to a maximum of 1.83 at 15,000 cycles and then decreased gradually. The graph for the drilled specimens showed less scatter than that for the plain specimens.
    Type: NACA-TN-955
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  • 148
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    Some investigations of the general instability of stiffened metal cylinders III : continuation of tests of wire-braced specimens and preliminary tests of sheet-covered specimens (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is the third of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The first five reports of this series cover investigations of the general instability problem under the loading conditions of pure bending and were prepared under the sponsorship of the Civil Aeronautics Administration. The succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics. This report is concerned primarily with the continuation of the tests of wire-braced specimens, and preliminary tests of sheet-covered specimens that had been made in the experimental investigation on the problem of the general instability of stiffened metal cylinders at the C.I.T.
    Type: NACA-TN-907
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  • 149
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    Some Investigations of the General Instability of Stiffened Metal Cylinders VI : Stiffened Metal Cylinders Subjected to Combined Bending and Transverse Shear (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is the sixth of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The first five reports of this series cover investigations of the general instability problem under the loading conditions of pure bending and were prepared under the sponsorship of the Civil Aeronautics Administration. This report and the succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics. This report summarizes the work that has been carried on in the experimental investigation of the problem of general instability of stiffened metal cylinders subjected to combined bending and transverse shear at the C.I.T. This part of the investigation includes tests on 55 sheet-covered specimens.
    Type: NACA-TN-910
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  • 150
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    Notes on the Stability and Control of Tailless Airplanes (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Problems involved in the stability and control of tailless airplanes are discussed. Such factors as the location of the aerodynamic center and its effect on the longitudinal stability, longitudinal trim with high-lift devices, the effects of various changes in the shape of the wing on lateral stability, and the effects of nacelles are covered. It appears that sufficient stability and controllability can be secured without sweepback. With sweepback, a flap over the center section of the wing may be used to serve the dual purpose of elevator control and high-lift device. Sweepback introduces undesirable stalling characteristics, however, and may require auxiliary devices to prevent stalling of the tips.
    Keywords: Aerodynamics
    Type: NACA-TN-837
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  • 151
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    Some Investigations of the General Instability of Stiffened Metal Cylinders IV : Continuation of Tests of Sheet-covered Specimens and Studies of the Buckling Phenomena of Unstiffened Circular Cylinders (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is the fourth of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The first five reports of this series cover investigations of the general instability problem under the loading conditions of pure bending and were prepared under the sponsorship of the Civil Aeronautics Administration. The succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics. This report is to deal primarily with the continuation of tests of sheet-covered specimens and studies of the buckling phenomena of unstiffened circular cylinders.
    Type: NACA-TN-908
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  • 152
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    Least-work analysis of the problem of shear lag in box beams (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The distribution of stress in the cover sheets of thin-wall box beams is analyzed, with regard to the effect of shear deformation in the cover sheets, by the method of least work. Explicit results are obtained for a number of representative cases that show the influence of the following factors on the stress patterns. (1) Variation of stress in spanwise direction as given by elementary beam theory. (2) Value of a parameter called shear-lag aspect ratio which designates the product of span-width ratio of the beam and of the square root of the ratio of effective shear modulus and tensing modulus of the cover sheets. (3) Value of ratio of cover-sheet stiffness to side-web stiffness. (4) Variation of beam height in span direction. (5) Variation of beam width in span direction. (6) Variation of cover-sheet thickness in span direction. General conclusions are drawn from the results obtained. Among them the most important one appears to be the fact that the shear-lag effect depends primarily on the following tow quantities: (1) the value of the shear-lag aspect ratio. (2) the shape of the curve representing the product of the stress of elementary beam theory and of the cover-sheet thickness.
    Type: NACA-TN-893
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  • 153
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    The exact solution of shear-lag problems in flat panels and box beams assumed rigid in the transverse direction (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical procedure is herein developed for obtaining exact solutions of shear-lag problems in flat panels and box beams: the method is based on the assumption that the amount of stretching of the sheets in the direction perpendicular to the direction of essential normal stresses is negligible. Explicit solutions, including the treatment of cut-outs, are given for several cases and numerical results are presented in graphic and tabular form. The general theory is presented in a from which further solutions can be readily obtained. The extension of the theory to cover certain cases of non-uniform cross section is indicated. Although the solutions are obtained in terms of infinite series, the present developments differ from those previously given in that, in practical cases, the series usually converge so rapidly that sufficient accuracy is afforded by a small number of terms. Comparisons are made in several cases between the present results and the corresponding solutions obtained by approximate procedures devised by Reissner and by Kuhn and Chiarito.
    Type: NACA-TN-894
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  • 154
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    Some investigations of the general instability of stiffened metal cylinders I : review of theory and bibliography (1943)
    In:  CASI
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    Publication Date: 2019-06-28
    Type: NACA-TN-905
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  • 155
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    Normal-pressure Tests of Circular Plates with Clamped Edges (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A fixture is described for making normal-pressure tests of flat plates 5 inches in diameter in which particular care was taken to obtain rigid clamping at the edges. Results are given for 19 plates, ranging in thickness from 0.015 to 0.072 inch. The center deflections and the extreme-fiber stresses at low pressures were found to agree with theoretical values; the center deflections at high pressures were 4 to 12 percent greater than the theoretical values. Empirical curves are derived of the pressure for the beginning of permanent set as a function of the dimensions of the plate and the tensile properties of the material.
    Type: NACA-TN-848
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  • 156
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    Adaptor for Measuring Principal Strains with Tuckerman Strain Gage (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An adapter is described which uses three Tuckerman optical strain gages to measure the displacement of the three vortices of an equilateral triangle along lines 120 degrees apart. These displacements are substituted in well-known equations in order to compute the magnitude and direction of the principal strains. Tests of the adaptor indicate that principal strains over a gage length of 1.42 inch may be measured with a systematic error not exceeding 4 percent and a mean observational error of the order of + or minus 0.000006. The maximum observed error in strain was of the order of 0.00006. The directions of principal strains for unidirectional stress were measured with the adaptor with an average error of the order of 1 degree.
    Type: NACA-TN-898
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  • 157
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    Determination of control-surface characteristics from NACA plain-flap and tab data (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The data from previous NACA pressure-distribution investigations of plain flaps and tabs have been analyzed and are presented in this paper in a form readily applicable to the problems of control-surface design. The experimentally determined variation of aerodynamic parameters with flap chord and tab chord are given in chart form and comparisons are made with the theory. With the aid of these charts and the theoretical relationships for a thin airfoil, the aerodynamic characteristics for control surfaces of any plan form with plain flaps and tabs may be determined. A discussion of the basic equations of the thin-airfoil theory and the development of a number of additional equations that will be helpful in tail design are presented in the appendixes. The procedure for applying the data is described and a sample problem of tail design is included. The data presented and the method of application set forth in this report should provide a reasonably accurate and satisfactory means of computing the aerodynamic characteristics of control surfaces.
    Type: NACA-TN-796
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  • 158
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    Bending with large deflection of a clamped rectangular plate with length-width ratio of 1.5 under normal pressure (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Von Karman equations for a thin flat plate with large deflections are solved for the special case of a plate with clamped edges having a ratio of length to width of 1.5 and loaded by uniform normal pressure. Center deflections, membrane stresses, and extreme-fiber bending stresses are given as a function of pressure for center deflections up to twice the thickness of the plate. For small deflections the results coincide with those obtained by Hencky from the linear theory. The maximum stresses and center deflection at high pressures differ less than 3 percent from those derived by Bostnov for an infinitely long plate with clamped edges. This agreement suggests that clamped plates with a length-to-width ratio greater than 1.5 may be reared as infinitely long plates for purposes of design.
    Type: NACA-TN-853
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  • 159
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    Stability of elastically supported columns (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A criterion is developed for the stiffness required of elastic lateral supports at the ends of a compression member to provide stability. A method based on this criterion is then developed for checking the stability of a continuous beam-column. A related method is also developed for checking the stability of a member of a pin-jointed truss against rotation in the plane of the truss.
    Type: NACA-TN-871
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  • 160
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    Damping characteristics of dashpots (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the damping characteristics of dashpots was carried out combining theory and experiment. Laminar flow was assumed and three equations for the steady velocity of a piston moving in a cylinder filled with liquid were derived. In the first equation, the piston was assumed coaxial in the cylinder and, in the second equation, the piston was assumed eccentric in the cylinder with an element of the piston in contact with the cylinder wall. The third equation is for a piston of circular cross section in an elliptical cylinder. Experiments showed that the piston is normally eccentric in the cylinder. The pistons tested were 1.25 and 2 inches in diameter 0.062 to 1.00 inch long, and the clearances varied from 1.36 to 5.16 x 10 to the 3rd power inch. The difference in pressure on the two sides of the piston varied from about 2 to 55 pounds per square inch. The piston velocities for each assembly were measured with damping liquids of three different viscosities. At high piston velocities, when turbulent flow exists, the observed velocities were much lower than the velocities calculated on the basis of laminar flow. Results for a wide range of Reynolds numbers are presented in graphical form.
    Type: NACA-TN-830
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  • 161
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    Square plate with clamped edges under normal pressure producing large deflections (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theoretical analysis is given for the stresses and deflections of a square plate with clamped edges under normal pressure producing large deflections. Values of the bending stress and membrane stress at the center of the plate and at the midpoint of the edge are given for center deflections up to 1.9 times the plate thickness. The shape of the deflected surface is given for low pressures and for the highest pressure considered. Convergence of the solution is considered and it is estimated that the possible error is less than 2 percent. The results are compared with the only previous approximate analysis known to the author and agree within 5 percent. They are also shown to compare favorably with the known exact solutions for the long rectangular plate and the circular plate.
    Type: NACA-TN-847
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  • 162
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    Stress distribution in and equivalent width of flanges of wide, thin-wall steel beams (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The use of different forms of wide-flange, thin-wall steel beams is becoming increasingly widespread. Part of the information necessary for a national design of such members is the knowledge of the stress distribution in and the equivalent width of the flanges of such beams. This problem is analyzed in this paper on the basis of the theory of plane stress. As a result, tables and curves are given from which the equivalent width of any given beam can be read directly for use in practical design. An investigation is given of the limitations of this analysis due to the fact that extremely wide and thin flanges tend to curve out of their plane toward the neutral axis. A summary of test data confirms very satisfactorily the analytical results.
    Type: NACA-TN-784
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  • 163
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    Data on Material Properties and Panel Compressive Strength of a Plastic-bonded Material of Glass Cloth and Canvas (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are presented of tests for determining the tensile, compressive, and bending properties of a material of plastic-bonding glass cloth and canvas layers. In addition, 10 panel specimens were tested in compression. Although the material is not satisfactory for primary structural use in aircraft when compared on a strength-weight basis with other materials in common use, there appears to be potential strength in the material that will require research for development. These points are considered in some detail in the concluding discussion of the report. An appendix shows that a higher tensile strength can be obtained by changes in the type of weave used in the glass-cloth reinforcement.
    Type: NACA-TN-975
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  • 164
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    The Influence of the Aerodynamic Span Effect on the Magnitude of the Torsional-divergence Velocity and on the Shape of the Corresponding Deflection Mode (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A procedure which takes into account the aerodynamic span effect is given for the determination of the torsional-divergence velocities of monoplanes. The explicit solutions obtained in several cases indicate that the aerodynamic span effect may increase the divergence velocities found by means of the section-force theory by as much as 17 to 40 percent. It is found that the magnitude of the effect increases with increasing degree of stiffness taper and decreases with increasing degree of chord taper. By a slight extension of the present method it is possible to analyze the elastic deformations of wings, and the resultant lift distributions, before torsional divergence occurs.
    Type: NACA-TN-926
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  • 165
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    Effects of Range of Stress and of Special Notches on Fatigue Properties of Aluminum Alloys Suitable for Airplane Propellers (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Laboratory tests were made to obtain information on the load-resisting properties of X76S-T aluminum alloy when subjected to static, impact, and repeated loads. Results are presented from static-load test of unnotched specimens in tension and in torsion and of notched specimens in tension. Charpy impact values obtained from bend tests on notched specimens and tension impact values for both notched and unnotched specimens tested at several different temperatures are included. The endurance limits obtained from repeated bending fatigue tests made on three different types of testing machine are given for unnotched polished specimens, and the endurance limits of notched specimens subjected to six different ranges of bending stress are also reported. The results indicated that: (a) polished rectangular specimens had an endurance limit about 30 percent less than that obtained for round specimens; (b) a comparison of endurance limits obtained from tests on three different types of machine indicated that there was no apparent effect of speed of testing on the endurance limit for the range of speeds used (1,750 to 13,000 rpm). (c) the fatigue strength (endurance limit) of the X76S-T alloy was greatly decreased by the presence of a notch in the specimens; (d) no complete fractures of the entire specimens occurred in notched fatigue specimens when subjected to stress cycles for which the mean stress at the notch during the cycle was a compressive stress; for this test condition a microscopic cracking occurred near the root of the notch and was used as a criterion of failure of the specimen. (e) as the mean stress at the notch was decreased from a tensile (+) stress to a compressive (-) stress, it was found that the alternating stress that could be superimposed on the mean stress in the cycle without causing failure of the specimens was increased.
    Type: NACA-TN-852
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  • 166
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    Requirements for Auxiliary Stiffeners Attached to Panels Under Combined Compression and Shear (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Panels of aluminum alloy sheets, framed by side and end stiffeners, were subjected to combined loading by means of offset knife edges applying loads to top and bottom end plates with reacting forces against the end plates supplied by laterally acting rollers. The test specimens were 17S-T aluminum alloy shoots 0.040 inch thick in panels of 10-inch width and three different lengths (approximately 10, 26, and 30 inch). Data were obtained for the bowing of transverse and longitudinal ribs of rectangular cross section and varying depths mounted on one side of the sheet only, for several ratios of compression to shear loads. Limiting values of the moments of inertia were calculated from these measurements. The experimental values exceed the theoretical values given by Timoshenko for the case of simply supported sheets with uniformly distributed boundary stresses. The work reported includes measurements of the effective shear moduli of the nine test panels with and without ribs. These data are compared with values published by Lahdo and Wagner.
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  • 167
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    Some Comparative Tests of Plain and Alclad 24S-T Sheet (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-821
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  • 168
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    The tensile elastic properties at low temperatures of 18:8 Cr-Ni steel as affected by heat treatment and slight plastic deformation (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-818
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  • 169
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    Application of the methods of gas dynamics to water flows with free surface I : flows with no energy dissipation (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The application is treated in sufficient detail to facilitate as much as possible its application by the engineer who is less familiar with the subject. The present work was undertaken with two objects in view. In the first place, it is considered as a contribution to the water analogy of gas flows, and secondly, a large portion is devoted to the general theory of the two-dimensional supersonic flows.
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  • 170
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    Application of the Methods of Gas Dynamics to Water Flows with Free Surface II : Flows with Momentum Discontinuities (hydraulic Jumps) (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this paper an introduction to shock polar diagrams is given which then leads into an examination of water depths in hydraulic jumps. Energy loss during these jumps is considered along with an extended look at elementary solutions of flow. An experimental test set-up is described and the results presented.
    Type: NACA-TM-935
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  • 171
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    Tests of Lead-bronze Bearings in the DVL Bearing-testing Machine (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The lead-bronze bearings tested in the DVL machine have proven themselves very sensitive to load changes as in comparison with bearings of light metal. In order to prevent surface injuries and consequently running interruptions, the increase of the load has to be made in small steps with sufficient run-in time between steps. The absence of lead in the running surface, impurities in the alloy (especially iron) and surface irregularities (pores) decreases the load-carrying capacity of the bearing to two or three times that of the static load.
    Type: NACA-TM-943
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  • 172
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    The Design of Jet Pumps (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report shows that by applying both energy and impulse theorems the optimum throat dimension of the mixing nozzle and the best shape of intake can be predicted approximately in a relatively simple manner. The necessary length of the mixing nozzle follows from Prandtl's turbulent mixing theory. The calculations are carried out for the mixing of similar and dissimilar fluids.
    Type: NACA-TM-982
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  • 173
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    Factors Influencing the Fatigue Strength of Materials (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A number of factors are considered which influence the static and fatigue strength of materials under practical operating conditions as contrasted with the relations obtaining under conditions of the usual testing procedure. Such factors are interruptions in operation, periodically fluctuating stress limits and mean stresses with periodic succession of several groups and stress states, statistical changes and succession of stress limits and mean stresses, frictional corrosion at junctures, and notch effects.
    Type: NACA-TM-987
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  • 174
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    Researches on direct injection in internal-combustion engines (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These researches present a solution for reducing the fatigue of the Diesel engine by permitting the preservation of its components and, at the same time, raising its specific horsepower to a par with that of carburetor engines, while maintaining for the Diesel engine its perogative of burning heavy fuel under optimum economical conditions. The feeding of Diesel engines by injection pumps actuated by engine compression achieves the required high speeds of injection readily and permits rigorous control of the combustible charge introduced into each cylinder and of the peak pressure in the resultant cycle.
    Type: NACA-TM-993
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  • 175
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    The Creep of Laminated Synthetic Resin Plastics (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The long-time loading strength of a number of laminated synthetic resin plastics was ascertained and the effect of molding pressure and resin content determined. The best value was observed with a 30 to 40 percent resin content. The long-time loading strength also increases with increasing molding pressure up to 250 kg/cm(exp 2); a further rise in pressure affords no further substantial improvement. The creep strength is defined as the load which in the hundredth hour of loading produces a rate of elongation of 5 X 10(exp -4) percent per hour. The creep strength values of different materials were determined and tabulated. The effect of humidity during long-term tests is pointed out.
    Type: NACA-TM-995
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  • 176
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    Inertia of dynamic pressure arrays (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: From earlier measurements and the mathematical examples, it can be gathered that the inertia of dynamic pressure arrays can be computed with sufficient accuracy and the proper size of tubing established, provided that certain requirements are made on the inertia.
    Type: NACA-TM-998
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  • 177
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    Stress Analysis of Circular Frames (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stresses in circular frames of constant bending stiffnesses, as encountered in thin-wall shells, are investigated from the point of view of finite depth of sectional area of frame. The solution is carried out for four fundamental load conditions. The method is illustrated on a worked out example.
    Keywords: Structural Mechanics
    Type: NACA-TM-999
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  • 178
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    The resistance coefficient of commercial round wire grids (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The resistance coefficients of commercial types of round wire grids were examined for the purpose of obtaining the necessary data on supercharger test stands for throttling the inducted air to a pressure corresponding to a desired air density. The measurements of the coefficients ranged up to Reynolds numbers of 1000. In the arrangement of two grids in tandem, which was necessary in order to obtain high resistance coefficients with the solidity, that is, mesh density of grid, was found to be accompanied by a further relationship with the mutual spacing of the individual grids.
    Type: NACA-TM-1003
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  • 179
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    The design of propeller blade roots (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Predicated on the assumption of certain normal conditions for engine and propeller, simple expressions for the static and dynamic stresses of propeller blade roots are evolved. They, in combination with the fatigue strength diagram of the employed material, afford for each engine power one certain operating point by which the state of stress serving as a basis for the design of the root is defined. Different stress cases must be analyzed, depending on the vibration tendency of engine and use of propeller. The solution affords an insight into the possible introduction of different size classes of propeller.
    Type: NACA-TM-1001
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  • 180
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    General airfoil theory (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: On the assumption of infinitely small disturbances the author develops a generalized integral equation of airfoil theory which is applicable to any motion and compressible fluid. Successive specializations yield various simpler integral equations, such as Possio's, Birnbaum's, and Prandtl's integral equations, as well as new ones for the wing of infinite span with periodic downwash distribution and for the oscillating wing with high aspect ratio. Lastly, several solutions and methods for solving these integral equations are give.
    Type: NACA-TM-979
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  • 181
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    New frictional resistance law for smooth plates (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: From measurements in the free boundary layer of a plate the laws governing the velocity distribution and a new resistance law are derived which, by increasing Reynolds number Re(sub x) afford lower resistance values than the logarithmic law. The transverse velocities, the shearing stress, and the mixing path profiles were also defined.
    Type: NACA-TM-986
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  • 182
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    Materials for Slack Diaphragms (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report deals with systematic experiments carried out on five diaphragm materials with different pretreatment, for the purpose of ascertaining the suitability of such materials for slack diaphragms. The relationship of deflection and load, temperature and moisture, was recorded. Of the explored materials, synthetic leather, balloon cloth, goldbeaters skin, Igelit and Buna, synthetic leather treated with castor oil is the most suitable material for the small pressure range required. Balloon cloth is nearly as good, while goldbeaters skin, Igelit and Buna were found to be below the required standards.
    Type: NACA-TM-964
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  • 183
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    Stagnation Temperature Recording (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report deals with the development of a thermometer for recording stagnation temperature in compressible mediums in turbulent flow within 1 to 2 percent error of the adiabatic temperature in the stagnation point, depending upon the speed. This was achieved by placing the junction of a thermocouple near the stagnation point of an aerodynamically beneficial body, special care being taken to assure an uninterrupted supply of fresh compressed air on the junction together with the use of metals of low thermal conductivity, thus keeping heat-transfer and heat-dissipation losses to a minimum. In other experiments the use of the plate thermometer was proved unsuitable for practical measurements by reason of its profound influence in the reading by the Reynolds number and by the direction of flow.
    Type: NACA-TM-967
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  • 184
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    Potential flow through centrifugal pumps and turbines (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The methods of conformal transformation up to the present have been applied to the potential flows in the rotation of solid bodies only to a limited extent. This report deals with aspects of centrifugal pumps and turbines such as: the complex potential for rotation, potential for the flow due to the blade rotation, velocities at the blade tip, comparison with "infinite number of blades," and a variable number of blades.
    Type: NACA-TM-973
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  • 185
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    Boundary layer removal by suction (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight-test data and wind-tunnel data on suction profiles are substantially in agreement. The lift values found in the model test can be actually flown and used as a basis for the design. To visualize the action of the suction, the flow conditions with and without suction on the upper surface were photographed; figures 12 to 15 are sections of the film.
    Type: NACA-TM-974
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  • 186
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    The oscillating wing with aerodynamically balanced elevator (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The two-dimensional problem of the oscillating wing with aerodynamically balanced elevator is treated in the manner that the wing is replaced by a plate with bends and stages and the airfoil section by a mean line consisting of one or more straights. The computed formulas and tables permit, on these premises, the prediction of the pressure distribution and of the aerodynamic reactions of oscillating elevators and tabs with any position of elevator hinge in respect to elevator leading edge.
    Type: NACA-TM-991
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  • 187
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    Corrections on the Thermometer Reading in an Air Stream (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method is described for checking a correction formula, based partly on theoretical considerations, for adiabatic compression and friction in flight tests and determining the value of the constant. It is necessary to apply a threefold correction to each thermometer reading. They are a correction for adiabatic compression, friction and for time lag.
    Type: NACA-TM-956
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  • 188
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    General Relationships Between the Various Systems of Reference Axes Employed in Flight Mechanics (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The different possibilities of orientation of the systems of axes currently employed in flight mechanics are compiled and described. Of the three possible couplings between the wind and aircraft axes, the most suitable coupling is that in which the y axis is made the principal axis of rotation for one of the two coupling angles (angles of attack). In connection with this coupling, an experimental system of axes is introduced, whose axes x(sub e) and z(sub e) are situated in the plane of symmetry of the airplane and rotate about the airplane lateral axis y = y(sub e). This system of axes enables the utilization of the coefficients obtained in the wind tunnel in the flight-mechanic equations by a simple transformation, with the aid of the angle of attack, measured in the plane of symmetry of the airplane.
    Type: NACA-TM-958
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  • 189
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    Chordwise load distribution of a simple rectangular wing (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The chordwise distribution theory was taken over from the theory of the infinite wing. Since in this work a series expansion in b/t was used, the computation converges only for large aspect ratios. In this paper a useful approximate solution will be found also for wings with large chord - i.e., small aspect ratio.
    Type: NACA-TM-963
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  • 190
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    Experiences with Flow-direction Instruments (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The method of recording the direction of flows on the basis of the hydrodynamic zero-point measurement has now reached a certain limit, in spite of the good results achieved. While the available flow-direction devices are accurate enough for many purposes, they are all insufficient for perfectly exact prediction of the flow direction. The next problem will be to achieve a point-by point flow-direction record, whereby the test procedure must be simplified, accelerated, and the degree of accuracy of the test data improved.
    Type: NACA-TM-969
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  • 191
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    Use of charts for flow discharge calculations (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Various problems in connection with engine design involve flow-discharge calculations which are rendered difficult both on account of the large number of external variables that enter into the computation - i.e., changes in discharge area during the process, change in volume of the cylinder, pressure, etc., and changes in the thermal constants themselves of the flow medium. A fairly accurate solution that does not involve an excessive amount of labor can be obtained only through the extensive use of i-s tables. In the present report, a solution is offered in the form of a different method making use of the I-S table of Lutz and Wolf.
    Type: NACA-TM-972
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  • 192
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    Present and Future Problems of Airplane Propulsion (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some of the problems considered in this report include: thermodynamics of surface friction, application of thick wing sections, special applications of controllable propellers, and gas turbines for aircraft.
    Type: NACA-TM-976
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  • 193
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    Air Transport by Gliders : Some Technical Observations (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This short analysis may be useful in determining the real tactical possibilities of "glider trains" and in adopting the course to be followed in possible studies of these questions. In this analysis most prominent are: (a) the power required for the train in level flight; (b) its speed; (c) climb; and (d) the type of airplane best suited for towing as well as design requirements for transport gliders.
    Type: NACA-TM-980
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  • 194
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    Recent Results in Rocket Flight Technique (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The concept of the effective ejection velocity of a rocket engine is explained and the magnitude of the attainable ejection velocity theoretically and experimentally investigated. Velocities above 3000 meters per second (6700 mph) are actually measured and the possibilities of further increases shown.
    Type: NACA-TM-1012
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  • 195
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    Theory of heat transfer and hydraulic resistance of oil radiators (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the present report the coefficients of heat transfer and hydraulic resistance are theoretically obtained for the case of laminar flow of a heated viscous liquid in a narrow rectangular channel. The results obtained are applied to the computation of oil radiators, which to a first approximation may be considered as made up of a system of such channels. In conclusion, a comparison is given of the theoretical with the experimental results obtained from tests on airplane oil radiators.
    Type: NACA-TM-1020
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  • 196
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    Integral methods in the theory of the boundary layer (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The application of the well-known basic principle of mechanics, the principle of Jourdain, to problems of the theory of the boundary layerleads tp an equation from which the equations of Von Karman, Leibenson, and Golubev are derived as special cases. The given equation may be employed in other integral methods. The present paper deals with the method of the variation of the thickness of the boundary layer. A number of new approximate formulas valuable in aerodynamic calculations for the fristion distribution are derived from this procedure. The method has been applied only to laminar boundary layers, but it seems probable that it may be generalized to include turbulent layers as well.
    Type: NACA-TM-1070
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  • 197
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    The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-A-41 , NACA-ARR-3E28
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  • 198
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    Protection of Nonmetallic Aircraft from Lightning III : Electrical Effects in Glider Towlines (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-W-62
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  • 199
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    Generalized Selection Charts for Bombers Powered by Two, Four, and Six 3000-horsepower Engines I : Capacity and Economy (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-672
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  • 200
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    General porpoising tests on flying-boat-hull models (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-W-96
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