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  • 1
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    Geophysics as a science (1937)
    In:  Geophysics, Milano, Gustav Fischer, vol. 2, no. 3, pp. 185-187, pp. L24306, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1937
    Keywords: Review article
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Geophysics as a science (1937)
    In:  Petroleum Eng., Milano, Gustav Fischer, vol. 8, no. 6, pp. 78, pp. L24306, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1937
    Keywords: Review article
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    On supposed regional variations in travel times (1937)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 27, no. 6, pp. 337-348, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1937
    Keywords: Travel time ; Velocity analysis ; Inhomogeneity ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Materials for the study of deep-focus earthquakes (second paper) (1937)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 27, no. 6, pp. 157-184, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1937
    Keywords: Seismology ; Hypocentral depth ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Geophysical investigation of Yosemite Valley (1937)
    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 27, no. 6, pp. 240, pp. L24306, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1937
    Keywords: Applied geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    On the integration of the thermoelastic equations (1937)
    In:  Phil. Mag., Bonn, Pergamon, vol. 7, no. 2, pp. 1017-1032, pp. B05S04, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1937
    Keywords: Elasticity ; temperature
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    More about earthquakes (1937)
    In:  The Sky, Milano, Gustav Fischer, vol. 2, no. 6, pp. 12-13, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1937
    Keywords: Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Progress in geophysical prospecting (1937)
    In:  Petroleum World, Annual Review, Milano, Gustav Fischer, vol. 34, no. 6, pp. 12-13, pp. L24306, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1937
    Keywords: Applied geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Witterung und Pflanzenwachstum im Jahre 1936 unter besonderer Berücksichtigung Bayerns (1937)
    In:  Prakt. Blätt. Pflanzenb. u. –schutz 14;p. 343-348
    Details
    Publication Date: 1937
    Description: Der Autor schildert detailliert den Witterungsverlauf des Vegetationsjahres 1935/36, gibt eine kleine Übersicht über die aufgetretenen Pflanzenkarankheiten und -schädlinge und bringt beides ansatzweise in einen Zusammenhang. Zudem listet er die Erträge des Vegetationsjahres auf und beurteilt diese. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Bayern ; 1936 ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Wachstum ; Witterung ; Hackfrüchte ; Hochwasser
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    BIBLIOGRAPHY INKA BB
  • 10
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    Über die Abhängigkeit der Obsterträge von Temperatur und Niederschlag (1937)
    In:  Die Gartenbauwissenschaft 10: 289-353
    Details
    Publication Date: 1937
    Description: Beschreibung der Beziehungen zwischen Ernteerträgen und der Witterung (Temperatur und Niederschlag mithilfe der Rangordungsmethode nach Holdefleiss) in 2 unterschiedlich klimatischen Regionen, Bestimmung von kritischen Zeiten, Auswirkungen auf die Obstsorten und -arten. KATASTER-BESCHREIBUNG: Faktoren Niederschlag und Temperatur haben zu bestimmten Zeiten wichtige Funktionen, schwanken aber zwischen den Arten und Sorten, jedoch Niederschlag ab Mai gewinnt umso mehr an Bedeutung, je geringer die Wasserspeicherkapazität des Bodens, höchster Wasserbedarf im Mai/Juni KATASTER-DETAIL: Delta Temp+ (April im Erntejahr), dann Ertrag ++ Delta Nied Juni (〉63mm Mittel von 1928-33 in Dahlem), dann Ertrag Gravensteiner 〉 115kg Delta Nied+ und Delta Temp+ (Juli-August im Vorjahr), dann Ertrag ++ Delta Nied- (Juli-August im aktuellen Jahr, , dann Ertrag -
    Keywords: Berlin, Hohenheim ; 1909-33, 1907-28 ; Apfel ; Ertrag ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Birne
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    BIBLIOGRAPHY INKA BB
  • 11
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    Feldberegnung und Getreidebau (1937)
    In:  Der Forschungsdienst 2: 581-587
    Details
    Publication Date: 1937
    Description: Effekt der Zusatzberegnung auf den Ertrag von Hafer KATASTER-BESCHREIBUNG: Erste Versuche zur Bestimmung des Beregnungszeitpunktes von Getreide KATASTER-DETAIL: Delta Nied+ (Mai 〉 73mm), dann kein Effekt einer zusätzlichen Beregnung auf Ertrag bei Hafer und Gerste (Jahr 1931 und 1932)
    Keywords: Berlin, Brandenburg ; 1934 ; Ertrag ; Hafer ; Niederschlag ; Trockenheit ; Gerste
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  • 12
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    Über die Malaria-Epidemie an der Nordseeküste 1826 (1937)
    In:  Zeitschrift für Hygiene und Infektionskrankheiten 120, 36
    Details
    Publication Date: 1937
    Description: 10 000 Erkrankungen und vielen Todesfällen, verursacht durch P. vivax und P. falciparum KATASTER-BESCHREIBUNG: der Sommer war so heiß gewesen, dass eine Übertragung der Erreger der Malaria tropica möglich war KATASTER-DETAIL:
    Keywords: Norddeutschland ; 1826 ; Umweltmedizin ; Infektionskrankheiten
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    BIBLIOGRAPHY INKA BB
  • 13
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    Der Einfluß der Witterung und Stickstoffdüngung auf das Wachstum, den Ertrag und die Kornqualität von fünf Kurzstroh- und einem Langstrohroggen unter besonderer Berücksichtigung der Standfestigkeit (1937)
    In:  Landwirtschaftl. Jahrbuch 85:1-47
    Details
    Publication Date: 1937
    Description: Untersuchungen zur Bedeutung der Winterfeuchtigkeit für Roggen bis etwa zum Zeitpunkt des Ährenschiebens, Wechselwirkung Sonnenscheindauer, Temperatur und Niederschlag in unterschiedlichen phänologischen Stadien bei unterschiedlichen Roggensorten und variierender Stickstoffgabe KATASTER-BESCHREIBUNG: Einfluss der Witterung (Sonnenschein, Temperatur, Niederschlag)auf das Wachstum KATASTER-DETAIL: Delta Sonn -, dann Längenwachstum +; Winterfeuchtigkeit +, dann Wachstum +; Delta Nied (von N-Düngung bis Ährenschieben) - und Delta T (von N-Düngung bis Ährenschieben) +, dann Längenwachstum = max; Delta Nied (Hauptvegetationszeit) +, Delta T (Hauptvegetationszeit) -, Delta Sonn (Hauptvegetationszeit) -, dann Längenwachstum +; Delta Nied (Hauptvegetationszeit) + und Delta Wind (Hauptvegetationszeit) +, dann Lagerbildung +;
    Keywords: Brandenburg, Versuchsfeld Bornim bei Potsdam ; 1932-36 ; Ertrag ; Landwirtschaft ; Niederschlag ; Roggen ; Temperatur ; Wachstum ; Düngung
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  • 14
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    Die land- und volkswirtschaftliche Bedeutung von Dürrejahren im deutschen Anbaugebiet, kritisch untersucht auf Grund des Witterungsverlaufs im 20. Jahrhundert (1937)
    In:  Landwirtschaftl. Jahrbuch 84:378-430.
    Details
    Publication Date: 1937
    Description: Beziehung zwischen Witterungsverlauf und Ertragsleistung KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1900-1935
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    BIBLIOGRAPHY INKA BB
  • 15
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    The structure of the ocean basin as indicated by seismological data and earthquake epicenters (1937)
    National Academy of Science
    In:  Professional Paper, International aspects of oceanography, Washington D.C., National Academy of Science, vol. 3, no. VIIa, pp. 41-50, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1937
    Keywords: Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    Experimental apparatus for the study of propellers (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The apparatus consists of a universal balance with transmission at variable speeds from 300 to 5,000 rpm and a group directly coupled to the model for speeds of 5 to 30,000 revolutions. This new apparatus was also designed with a torsion meter for measuring the torque. Tests were conducted on the effect of the angle between the propeller axis and the wind direction. The results presented correspond to a first series of tests made without an interposed wing and in which the distance between the plane of the propeller disk and the tail was maintained constant.
    Type: NACA-TM-819
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    NASA TECHNICAL REPORTS
  • 17
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    Experimental Investigation of the Problem of Surface Roughness (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Based on the universal laws of turbulent velocity distribution at rough and smooth walls, there is in the present work presented a method that allows surface roughness tests and in particular, measurements on the roughness of ship surfaces to be carried out in a much simpler manner. The types of roughness investigated were in the form of flat, rough plates installed in a square-section rectangular channel, the other three walls always being smooth. Twenty-one plates of various roughness were investigated, the roughness elements being the following: spheres of diameter 0.41 and 0.21, respectively, spherical segments, cones, and "short" and "long" angles.
    Type: NACA-TM-823
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    NASA TECHNICAL REPORTS
  • 18
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    Helicopter problems (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report deals with a number of the main problems requiring solution in the development of helicopters and concerning the lift, flying performance, stability, and drive. A complete solution is given for the stability of the helicopter with rigid blades and control surfaces. With a view to making a direct-lift propeller sufficient without the addition of auxiliary propellers, the "flapping drive" is assessed and its efficiency calculated.
    Type: NACA-TM-827
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Contributions to the theory of incomplete tension bay (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report offers an approximate theory for the stress and deformation condition after buckling of the skin in reinforced panels and shells loaded in simple shear and compression and under combined stresses. The theory presents a unified scheme for stresses of these types. It is based upon the concept of a nonuniform stress distribution in the metal panel and its marked power of resistance against compressive stresses ("incomplete" tension bay).
    Type: NACA-TM-831
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    NASA TECHNICAL REPORTS
  • 20
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    The Strength of Shell Bodies : Theory and Practice (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The monocoque form of airplane construction has introduced a number of new problems to the stress calculator and the designer. The problems for the stress calculator fall into two groups: the determination of the stress condition (shell statics) and the determination of the failing strength (shell strength). The present report summarizes the most important theoretical and experimental results on this subject.
    Type: NACA-TM-838
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    NASA TECHNICAL REPORTS
  • 21
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    Detonation and Autoignition : Some Considerations on Methods of Determination (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is a critical analysis of the methods of determination of the tendency to detonation. No attempt has been made to describe in detail the different fuels and the different methods proposed.
    Type: NACA-TM-843
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    NASA TECHNICAL REPORTS
  • 22
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    Wind-Tunnel and Flight Tests of Slot-lip Ailerons (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The slot-lip ailerons developed by the NACA consist of a flap-type spoiler with an adjoining continuously open slot. The ailerons were developed in an investigation of the delayed response, or lag, of spoiler-type lateral controls. This report presents the results of tests of these slot-lip ailerons made on wing models in the 7 by 10-foot wind tunnel, on a Fairchild 22 airplane in the full-scale wind tunnel and in flight, and on the Weick W1-A airplane in flight.
    Type: NACA-TR-602
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 23
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    Spinning Characteristics of the XN2Y-1 Airplane Obtained from the Spinning Balance and Compared with Results from the Spinning Tunnel and from Flight Tests (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of tests of a 1/10-scale model of the XN2Y-1 airplane tested in the NACA 5-foot vertical wind tunnel in which the six components of forces and moments were measured. The model was tested in 17 attitudes in which the full-scale airplane had been observed to spin, in order to determine the effects of scale, tunnel, and interference. In addition, a series of tests was made to cover the range of angles of attack, angles of sideslip, rates of rotation, and control setting likely to be encountered by a spinning airplane. The data were used to estimate the probable attitudes in steady spins of an airplane in flight and of a model in the free-spinning tunnel. The estimated attitudes of steady spin were compared with attitudes measured in flight and in the spinning tunnel. The results indicate that corrections for certain scale and tunnel effects are necessary to estimate full-scale spinning attitudes from model results.
    Type: NACA-TR-607
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    NASA TECHNICAL REPORTS
  • 24
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    Aerodynamic Characteristics of NACA 23012 and 23021 Airfoils with 20-Percent-chord External-Airfoil Flaps of NACA 23012 Section (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation of the general aerodynamic characteristics of the NACA 23012 and 23021 airfoils, each equipped with a 0.20c external flap of NACA 23012 section. The tests were made in the NACA 7 by 10-foot and variable-density wind tunnels and covered a range of Reynolds numbers that included values corresponding to those for landing conditions of a wide range of airplanes. Besides a determination of the variation of lift and drag characteristics with position of the flap relative to the main airfoil, complete aerodynamic characteristics of the airfoil-flap combination with a flap hinge axis selected to give small hinge moments were measured in the two tunnels. Some measurements of air loads on the flap itself in the presence of the wing were made in the 7 by 10-foot wind tunnel.
    Type: NACA-TR-573
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    NASA TECHNICAL REPORTS
  • 25
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    Wing-Nacelle-Propeller Interference for Wings of Various Spans Force and Pressure-Distribution Tests (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of an experimental investigation made in the NACA full-scale wind tunnel to determine the effect of wing span on nacelle-propeller characteristics and, reciprocally, the lateral extent of nacelle and propeller influence on a monoplane wing. The results provide a check on the validity of the previous research on nacelles and propellers with 15-foot-span wings tested in the 20-foot wind tunnel and reported in technical reports 415, 462, 505, 506, and 507.
    Type: NACA-TR-569
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  • 26
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    The effect of lateral controls in producing motion of an airplane as computed from wind-tunnel data (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an analytical study of the lateral controllability of an airplane in which both the static rolling and yawing moments supplied by the controls and the reactions due to the inherent stability of the airplane have been taken into account. The investigation was undertaken partly for the purpose of coordinating the results of a long series of wind-tunnel investigations with phenomena observed in flight tests; for this reason a hypothetical average airplane, embodying the essential characteristics of both wind-tunnel models and the full-size test airplanes, was assumed for the study.
    Type: NACA-TR-570
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    NASA TECHNICAL REPORTS
  • 27
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    Measurements of Fuel Distribution Within Sprays for Fuel-Injection Engines (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two methods were used to measure fuel distribution within sprays from several types of fuel-injection nozzles. A small tube inserted through the wall of an air tight chamber into which the sprays were injected could be moved about inside the chamber. When the pressure was raised to obtain air densities of 6 and 14 atmospheres, some air was forced through the tube and the fuel that was carried with it was separated by absorbent cotton and weighed. Cross sections of sprays from plain, pintle, multiple-orifice, impinging-jets, centrifugal, lip, slit, and annular-orifice nozzles were investigated, at distances of 1, 3, 5, and 7 inches from the nozzles.
    Type: NACA-TR-565
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    NASA TECHNICAL REPORTS
  • 28
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    Ground-Handling Forces on a 1/40-scale Model of the U. S. Airship "Akron." (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of full-scale wind tunnel tests conducted to determine the ground-handling forces on a 1/40-scale model of the U. S. Airship "Akron." Ground-handling conditions were simulated by establishing a velocity gradient above a special ground board in the tunnel comparable with that encountered over a landing field. The tests were conducted at Reynolds numbers ranging from 5,000,000 to 19,000,000 at each of six angles of yaw between 0 degree and 180 degrees and at four heights of the model above the ground board. The ground-handling forces vary greatly with the angle of yaw and reach large values at appreciable angles of yaw. Small changes in height, pitch, or roll did not critically affect the forces on the model. In the range of Reynolds numbers tested, no significant variation of the forces with the scale was disclosed.
    Type: NACA-TR-566
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  • 29
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    Calculated and Measured Pressure Distributions over the Midspan Section of the NACA 4412 Airfoil (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are presented.
    Type: NACA-TR-563
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  • 30
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    A simplified application of the method of operators to the calculation of disturbed motions of an airplane (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simplified treatment of the application of Heaviside's operational methods to problems of airplane dynamics is given. Certain graphical methods and logarithmic formulas that lessen the amount of computation involved are explained. The problem representing a gust disturbance or control manipulation is taken up and it is pointed out that in certain cases arbitrary control manipulations may be dealt with as though they imposed specific constraints on the airplane, thus avoiding the necessity of any integration. The application of the calculations described in the text is illustrated by several examples chosen to show the use of the methods and the practicability of the graphical and logarithmic computations described.
    Type: NACA-TR-560
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  • 31
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    Wind-Tunnel Tests of 10-foot-diameter Autogiro Rotors (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a series of 10-foot-diameter autogiro rotor models tested in the NACA 20-foot wind tunnel. Four of the models differed only in the airfoil sections of the blades, the sections used being the NACA 0012, 0018, 4412, and 4418. Three additional models employing the NACA 0012 section were tested, in which a varying portion of the blade near the hub was replaced by a streamline tube with a chord of about one-fourth the blade chord.
    Type: NACA-TR-552
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  • 32
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    Aircraft compass characteristics (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A description of the test methods used at the National Bureau of Standards for determining the characteristics of aircraft compasses is given. The methods described are particularly applicable to compasses in which mineral oil is used as the damping liquid. Data on the viscosity and density of certain mineral oils used in United States Navy aircraft compasses are presented. Characteristics of Navy aircraft compasses IV to IX and some other compasses are shown for the range of temperatures experienced in flight. Results of flight tests are presented. These results indicate that the characteristic most desired in a steering compass is a short period and, in a check compass, a low overswing.
    Type: NACA-TR-551
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  • 33
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    Some effects of argon and helium upon explosions of carbon monoxide and oxygen (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation conducted to study the effects of the inert gases, argon and helium, upon flame speed and expansion ratio in exploding mixtures of carbon monoxide, oxygen and water.For the particular gas mixtures investigated the results show that: (1) With the possible exception of helium in small amounts the addition of inert gas always produces decreased flame speed and expansion ratio; (2) like volumes of argon and helium have very different effects upon flame speed but practically the same effect upon expansion ratio; and (3) the difference in the effect of these two gases upon speed is independent of the ratio of carbon monoxide to oxygen. A discussion of some possible modes by which inert gases may produce the observed effects is included.
    Type: NACA-TR-553
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    NASA TECHNICAL REPORTS
  • 34
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    Effect of tip shape and dihedral on lateral-stability characteristics (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of wind tunnel tests to determine the effect of wing-tip shape and dihedral on some of the aerodynamic characteristics of Clark Y wings that affect the performance and lateral stability of airplanes. Force tests at several angles of yaw and rotation tests at zero yaw were made. From these tests the rates of change of rolling moment, yawing moment, and cross-wind force coefficients with angle of yaw and the rate of change of rolling moment coefficient with rolling were determined.
    Type: NACA-TR-548
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  • 35
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    Experimental Investigation of Wind-Tunnel Interference on the Downwash Behind an Airfoil (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The interference of the wind-tunnel boundaries on the downwash behind an airfoil has been experimentally investigated and the results have been compared with the available theoretical results for open-throat wind tunnels. As in previous studies, the simplified theoretical treatment that assumes the test section to be an infinite free jet has been shown to be satisfactory at the lifting line. The experimental results, however, show that this assumption may lead to erroneous conclusions regarding the corrections to be applied to the downwash in the region behind the airfoil where the tail surfaces are normally located. The results of a theory based on the more accurate concept of the open-jet wind tunnel as a finite length of free jet provided with a closed exit passage are in good qualitative agreement with the experimental results.
    Type: NACA-TR-609
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  • 36
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    Stress Analysis of Beams with Shear Deformation of the Flanges (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report discusses the fundamental action of shear deformation of the flanges on the basis of simplifying assumptions. The theory is developed to the point of giving analytical solutions for simple cases of beams and of skin-stringer panels under axial load. Strain-gage tests on a tension panel and on a beam corresponding to these simple cases are described and the results are compared with analytical results. For wing beams, an approximate method of applying the theory is given. As an alternative, the construction of a mechanical analyzer is advocated.
    Type: NACA-TR-608
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  • 37
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    The Rolling Friction of Several Airplane Wheels and Tires and the Effect of Rolling Friction on Take-Off (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of test made to determine the rolling friction of airplane wheels and tires under various conditions of wheel loading, tire inflation pressure, and ground surface. The effect of wheel-bearing type was also investigated. Six pairs of wheels and tires were tested including two sizes of each of the types designated as standard (high pressure), low pressure, and extra low pressure. The results of calculations intended to show the effect of variations in rolling friction on take-off are also presented.
    Type: NACA-TR-583
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  • 38
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    Aircraft accidents.method of analysis (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is a revision of NACA-TR-357. It was prepared by the Committee on Aircraft Accidents. The purpose of this report is to provide a basis for the classification and comparison of aircraft accidents, both civil and military.
    Type: NACA-TR-576
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  • 39
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    Cooling Tests of a Single-Row Radial Engine with Several NACA Cowlings (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The cooling of a single-row radial air-cooled engine using several cowling arrangements has been studied in the NACA 20-foot wind tunnel. The results show the effect of the propeller and several cowling arrangements on cooling for various values of the indicated horsepower in the climb condition. A table giving comparative performance of the various cowling arrangements is presented. The dependence of temperature on indicated horsepower and pressure drop across the baffles is shown by charts. Other charts show the limiting indicated horsepower against the pressure drop across the engine and the heat dissipated at various values of the indicated horsepower.
    Type: NACA-TR-596
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  • 40
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    Full-Scale Tests of a New Type NACA Nose-Slot Cowling (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An extended experimental study has been made in regard to the various refinements in the design of engine cowlings as related to the propeller-nacelle unit as a whole, under conditions corresponding to take-off, climb, and normal flight. The tests were all conducted at full scale in the 20-foot wind tunnel. This report presents the results of a novel type of engine cowling, characterized by the fact that the exit opening discharging the cooling air is not, as usual, located behind the engine but at the foremost extremity or nose of the cowling. The efficiency is found to be high, owing to the fact that higher velocities may be used in the exit opening.
    Type: NACA-TR-595
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  • 41
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    Cooling of Airplane Engines at Low Air Speeds (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a comprehensive experimental study carried out at full scale in the NACA 20-foot wind tunnel, the general purpose of which is to furnish information in regard to the functioning of the power plant and propeller unit under different conditions. This report deals particularly with the problem of the cooling of an airplane engines on the ground. The influence of different nose forms, skirts, flaps, propellers, spinners, and special blowers has been investigated.
    Type: NACA-TR-593
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  • 42
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    Characteristics of Six Propellers Including the High-Speed Range (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation is part of an extensive experimental study that has been carried out at full scale in the NACA 20-foot tunnel, the purpose of which has been to furnish information in regard to the functioning of the propeller-cowling-nacelle unit under all conditions of take-off, climbing, and normal flight. This report presents the results of tests of six propellers in the normal and high-speed flight range and also includes a study of the take-off characteristics.
    Type: NACA-TR-594
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  • 43
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    Further Studies of Flame Movement and Pressure Development in an Engine Cylinder (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes an investigation using a stroboscopic apparatus for observing flame movement through a large number of small windows distributed over the head of a spark-ignition engine in following flame spread with combustion chambers of different shapes at two engine speed and for a variety of spark-plug locations including single and twin ignition. The principal factors influencing flame movement in the engine are discussed, and the lack of reliable information regarding their separate effects upon the structure of the flame and its speed of propagation are emphasized.
    Type: NACA-TR-556
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  • 44
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    Airfoil Section Characteristics as Affected by Variations of the Reynolds Number (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation of a systematically chosen representative group of related airfoils conducted in the NACA variable-density wind tunnel over a wide range of Reynolds number extending well into the flight range. The tests were made to provide information from which the variations of airfoil section characteristics with changes in the Reynolds number could be inferred and methods of allowing for these variations in practice could be determined. This work is one phase of an extensive and general airfoil investigation being conducted in the variable-density tunnel and extends the previously published researches concerning airfoil characteristics as affected by variations in airfoil profile determined at a single value of the Reynolds number.
    Type: NACA-TR-586
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  • 45
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    Measurements of Intensity and Scale of Wind-Tunnel Turbulence and Their Relation to the Critical Reynolds Number of Spheres (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The investigation of wind-tunnel turbulence, conducted at the National Bureau of Standards with the cooperation of the National Advisory Committee for Aeronautics, has been extended to include a new variable, namely, the scale of the turbulence. This report presents the results of a study of this new variable together with the intensity of the turbulence, and the effect of both on the critical Reynolds number of spheres.
    Type: NACA-TR-581
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  • 46
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    Effect of Nozzle Design on Fuel Spray and Flame Formation in a High-Speed Compression-Ignition Engine (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Fuel was injected from different type of injection nozzles into the combustion chamber of the NACA combustion apparatus, operated as a compression-ignition engine. High speed motion pictures were taken of the fuel sprays and combustion. Single-orifice nozzles of 0.008, 0.020, and 0.040 inch diameter, and multiorifice nozzles having 2, 6, and 16 orifices were tested. Nozzles having impinging jets and slit orifices were also included. The photographs indicate that the rate of vapor diffusion from the spray is comparatively slow and that this slow rate of diffusion for combustion chambers with little or no air flow prevents the compression-ignition engine from giving the high performance inherent in the high compression ratios. The sprays from the multiorifice nozzles destroyed the air movement to a greater extent than did those from single orifice nozzles. It is concluded that high performance cannot be realized until the methods of distributing the fuel are improved by means of the injection-nozzle design, air flow, or both.
    Type: NACA-TR-561
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  • 47
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    Free Spinning Wind-tunnel Tests of a Low-wing Monoplane with Systematic Wings and Tails (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-630
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  • 48
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    A Sound Pressure-level Meter Without Amplification (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The N.A.C.A. has developed a simple pressure-level meter for the measurement of sound-pressure levels above 70 db. The instrument employs a carbon microphone but has no amplification. The source of power is five flashlight batteries. Measurements may be made up to the threshold of feeling with an accuracy of plus or minus 2 db; band analysis of complex spectra may be made if desired.
    Type: NACA-TN-629
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  • 49
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    Plastics as structural materials for aircraft (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose here is to consider the mechanical characteristics of reinforced phenol-formaldehyde resin as related to its use as structural material for aircraft. Data and graphs that have appeared in the literature are reproduced to illustrate the comparative behavior of plastics and materials commonly used in aircraft construction. Materials are characterized as to density, static strength, modulus of elasticity, resistance to long-time loading, strength under repeated impact, energy absorption, corrosion resistance, and ease of fabrication.
    Type: NACA-TN-628
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  • 50
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    Pressure distribution over a Clark Y-H airfoil section with a split flap (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made in the N.A.C.A. 7 by 10 foot wind tunnel of the distribution of air pressure over one chord section of a Clark Y-H airfoil with a split flap. The results obtained are given in the form of diagrams showing the chordwise distribution of pressure on both airfoil and flap as plots of calculated aerodynamic coefficients for both airfoil and flap.
    Type: NACA-TN-627
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  • 51
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    Static Thrust Analysis of the Lifting Airscrew (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a combined theoretical and experimental investigation conducted at the Georgia School of Technology on the static thrust of the lifting air screw of the type used in modern autogiros and helicopters. The theoretical part of this study is based on Glauert's analysis but certain modifications are made that further clarify and simplify the problem. Of these changes the elimination of the solidity as an independent parameter is the most important. The experimental data were obtained from tests on four rotor models of two, four, and five blades and, in general, agree quite well with the theoretical calculations. The theory indicates a method of evaluating scale effects on lifting air screws, and these corrections have been applied to the model results to derive general full-scale static thrust, torque, and figure-of-merit curves for constant-chord, constant-incidence rotors. Convenient charts are included that enable hovering flight performance to be calculated rapidly.
    Type: NACA-TN-626
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  • 52
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    Spinning Characteristics of Wings IV : Changes in Stagger of Rectangular Clark Y Cellules (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-625
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  • 53
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    Bending Tests of Circular Cylinders of Corrugated Aluminum-alloy Sheet (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Bending tests were made of two circular cylinders of corrugated aluminum-alloy sheet. In each test failure occurred by bending of the corrugations in a plane normal to the skin. It was found, after analysis of the effect of short end bays, that the computed stress on the extreme fiber of a corrugated cylinder is in excess of that for a flat panel of the same basic pattern and panel length tested as a pin-ended column. It is concluded that this increased strength was due to the effects of curvature of the pitch line. It is also concluded from the tests that light bulkheads closely spaced strengthen corrugated cylinders very materially.
    Type: NACA-TN-595
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  • 54
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    Maximum Forces Applied by Pilots to Wheel-type Controls (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements were made of the maximum push, pull, and tangential forces that could be applied to airplane wheel-type controls for a wide range of fore-and-aft positions of the wheel. The measurements were conducted with several sizes of wheels and several heights of the center of the wheel above the seat. Various one and two-hand grips with pilots both secure and free were studied for each of the two pilots used in the investigation.
    Type: NACA-TN-623
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  • 55
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    Performance Characteristics of Venturi Tubes Used in Aircraft for Operating Air-driven Gyroscopic Instruments (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel and flight tests were made to determine the performance characteristics of two designs of commercially available venturi tubes used in airplanes to operate air-driven gyroscopic instruments. Data obtained at sea level may be used to make approximate predictions of performance at higher altitudes. There is some indication that this may also be done for single venturi tubes. For a given installation in which an air-driven instrument is connected through tubing with a venturi tube, the volume rate of induced air flow is approximately proportional to the product of indicated air speed and the square root of the ratio of standard to ambient air pressure. The efficiency of such a system at a given altitude is constant. Rather large variations in suction and efficiency were found for individual tubes of the same design. Cylindrical fairings on the external surface resulted in a reduction of both drag and suction but little change in efficiency.
    Type: NACA-TN-624
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  • 56
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    Tank tests of two models of flying-boat hulls to determine the effect of ventilating the step (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of tests made in the N.A.C.A. tank on two models of flying-boat hulls to determine the effect of ventilating the step are given graphically. The step of N.A.C.A. model 11-C was ventilated in several different ways and it was found that the resistance of the normal form is not appreciably affected by artificial ventilation in any of the forms tried. Further tests made with the depth of the step of model 11-C reduced likewise show no appreciable effect on the resistance from ventilation of the step. Tests were made on a model of the hull of the Navy P3M-1 flying-boat hull both with and without ventilation of the step. It was found that the discontinuity which is obtained in the resistance curves of this model is eliminated by ventilating the step.
    Type: NACA-TN-594
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  • 57
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    Flight Tests of an Airplane Showing Dependence of the Maximum Lift Coefficient on the Test Conditions (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data are presented to show the extent to which the maximum lift coefficient and consequently the minimum speed of an airplane, determined by flight tests, may vary with test conditions. The data show that cl-max may vary as much as 14 percent, depending on the altitude and wing loading at which the tests were made, the position or motion of the propeller, and the rate at which the angle of attack is changing when the maximum lift coefficient is obtained. The variation of the maximum lift coefficient with these factors, which are under the control of the test engineer, shows the need of standardizing the test procedure. A further variation is shown with wing conditions as affected by weathering and vibration, factors that cannot be completely controlled.
    Type: NACA-TN-622
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  • 58
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    Pressure Drop Across Finned Cylinders Enclosed in a Jacket (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The pressure drop across finned cylinders in a jacket for a range of air speeds from approximately 13 to 230 miles per hour has been investigated. Tests were made to determine the effect on the pressure drop of changes in fin space, fin width, jacket entrance and exit areas, skirt-approach radius, and the use of fillets and a separator plate at the rear of the cylinder. The pressure drop across the cylinder increased as the fin space decreased, the increase being very rapid at fin spaces smaller than approximately 0.20 inch. Fin width had little effect on the pressure drop for the range of widths tested. The pressure drop across the cylinder was nearly halved by increasing the skirt-approach radius from 3/4 inch to 1-1/4 inches, but fillets and a separator plate at the rear of the cylinder had little effect on the pressure drop. The pressure drop across a cylinder with tapered fins was greater than that for a cylinder having rectangular fins with the same effective fin spacing.
    Type: NACA-TN-621
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  • 59
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    A study of the factors affecting the range of airplanes (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made of the most important factors affecting the range of airplanes. Numerical examples are given showing the effects of different variables on the range of a two-engine airplane. The takeoff problems of long-range airplanes are analyzed.
    Type: NACA-TN-592
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  • 60
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    Pressure drop in tubing in aircraft instrument installations (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The theoretical basis of calculation of pressure drop in tubing is reviewed briefly. The effect of pressure drop in connecting tubing upon the operation and indication of aircraft instruments is discussed. Approximate equations are developed, and charts and tables based upon them are presented for use in designing installations of altimeters, air-speed indicators, rate-of-climb indicators, and air-driven gyroscopic instruments.
    Type: NACA-TN-593
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  • 61
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    Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that cooling can be improved by 20 percent by using a correctly designed baffle. Such a gain is as effective as a 65 percent increase in pressure drop across the standard baffle, which had a 1/4 inch clearance between baffle and fin tips.
    Type: NACA-TN-620
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  • 62
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    Compression-ignition Engine Performance at Altitudes and at Various Air Pressures and Temperatures (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Engine test results are presented for simulated altitude conditions. A displaced-piston combustion chamber on a 5- by 7-inch single cylinder compression-ignition engine operating at 2,000 r.p.m. was used. Inlet air temperature equivalent to standard altitudes up to 14,000 feet were obtained. Comparison between performance at altitude of the unsupercharged compression-ignition engine compared favorably with the carburetor engine. Analysis of the results for which the inlet air temperature, inlet air pressure, and inlet and exhaust pressure were varied indicates that engine performance cannot be reliably corrected on the basis of inlet air density or weight of air charge. Engine power increases with inlet air pressure and decreases with inlet air temperatures very nearly as straight line relations over a wide range of air-fuel ratios. Correction factors are given.
    Type: NACA-TN-619
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  • 63
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    The Sonic Altimeter for Aircraft (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Discussed here are results already achieved with sonic altimeters in light of the theoretical possibilities of such instruments. From the information gained in this investigation, a procedure is outlined to determine whether or not a further development program is justified by the value of the sonic altimeter as an aircraft instrument. The information available in the literature is reviewed and condensed into a summary of sonic altimeter developments. Various methods of receiving the echo and timing the interval between the signal and the echo are considered. A theoretical discussion is given of sonic altimeter errors due to uncertainties in timing, variations in sound velocity, aircraft speed, location of the sending and receiving units, and inclinations of the flight path with respect to the ground surface. Plots are included which summarize the results in each case. An analysis is given of the effect of an inclined flight path on the frequency of the echo. A brief study of the acoustical phases of the sonic altimeter problem is carried through. The results of this analysis are used to predict approximately the maximum operating altitudes of a reasonably designed sonic altimeter under very good and very bad conditions. A final comparison is made between the estimated and experimental maximum operating altitudes which shows good agreement where quantitative information is available.
    Type: NACA-TN-611
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  • 64
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    Full Scale Span Load Distribution on a Tapered Wing with Split Flaps of Various Spans (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 airfoil equipped with 20 percent chord split trailing-edge flaps of various spans. A special installation was employed in the tests utilizing a half-span airfoil mounted vertically above a reflection plane. The airfoil has a constant chord center section and rounded tips and is tapered in thickness from 18 percent c at the root to 9 percent c at the tip. The aerodynamic characteristics, given by the usual dimension less coefficients, are presented graphically as functions of flap span and angle of attack as well as by semispan load diagrams. The results indicate, in general, that only a relatively small increase in the normal-force coefficient is to be expected by extending the flap span of an airfoil-flap combination, similar to the one tested, beyond 70 percent of the wing span.
    Type: NACA-TN-591
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  • 65
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    Considerations affecting the additional weight required in mass balance of ailerons (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is essentially a consideration of mass balance of ailerons from a preliminary design standpoint, in which the extra weight of the mass counterbalance is the most important phase of the problem. Equations are developed for the required balance weight for a simple aileron and this weight is correlated with the mass-balance coefficient. It is concluded the location of the c.g. of the basic aileron is of paramount importance and that complete mass balance imposes no great weight penalty if the aileron is designed to have its c.g. inherently near to the hinge axis.
    Type: NACA-TN-609
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  • 66
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    The Behavior of Thin-will Monocoque Cylinders Under Torsional Vibration (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Curves of forced frequency against amplitude are presented for the conditions where the forced frequency is both increased and decreased into the resonant range. On the basis of these curves it is shown that the practical resonance frequency is the point where wrinkling first occurs and that the resonance frequency will be subject to considerable travel once permanent wrinkles appear in the vibrating shell. The decreasing mode of striking resonance is found to be by far the most destructive condition.
    Type: NACA-TN-607
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  • 67
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    Effect of air-entry angle on performance of a 2-stroke-cycle compression-ignition engine (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine the effect of variations in the horizontal and vertical air-entry angles on the performance characteristics of a single-cylinder 2-stroke-cycle compression-ignition test engine. Performance data were obtained over a wide range of engine speed, scavenging pressure, fuel quantity, and injection advance angle with the optimum guide vanes. Friction and blower-power curves are included for calculating the indicated and net performances. The optimum horizontal air-entry angle was found to be 60 degrees from the radial and the optimum vertical angle to be zero, under which conditions a maximum power output of 77 gross brake horsepower for a specific fuel consumption of 0.52 pound per brake horsepower-hour was obtained at 1,800 r.p.m. and 16-1/2 inches of Hg scavenging pressure. The corresponding specific output was 0.65 gross brake horsepower per cubic inch of piston displacement. Tests revealed that the optimum scavenging pressure increased linearly with engine speed. The brake mean effective pressure increased uniformly with air quantity per cycle for any given vane angle and was independent of engine speed and scavenging pressure.
    Type: NACA-TN-610
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  • 68
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    Free-spinning Wind-tunnel Tests of a Low-wing Monoplane with Systemic Changes in Wings and Tails (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of tests was made at the National Advisory Committee for Aeronautics (NACA) free-spinning tunnel to determine the effect of systematic changes in wing and tail arrangement upon steady-spinning and recovery characteristics of a conventional low-wing monoplane model for a basic loading condition. Eight wings and three tails, covering a wide range of aerodynamic characteristics, were independently ballasted so as to be interchangeable with no change in mass distribution. For each of the 24 wing-tail combinations, observations were made of steady spins for four control settings and of recoveries for five control manipulators. The results are presented in the form of charts comparing the spin characteristics. The results showed that, with a poor tail arrangement, wing plan form and tip shape had a considerable effect on the spinning characteristics.
    Type: NACA-TN-608
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  • 69
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    Increasing the Strength of Aluminum-alloy Columns by Prestressing (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of tests was made in which the column strength of 17ST tubing was increased as much as 50 percent by prestressing the tubing to 40,000 pounds per square inch in compression under conditions of support that prevented column failure at this stress. This prestressing achieves it's beneficial effects entirely by improving the compressive properties of the material, principally the proportional limit.
    Type: NACA-TN-618
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  • 70
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    Hydrodynamic Tests in the N.A.C.A. Tank of a Model of the Hull of the Short Calcutta Flying Boat (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The hydrodynamic characteristics of a model of the hull of the Short Calcutta (N.A.C.A. Model 47) are presented in non-dimensional form. This model represents one of a series of hulls of successful foreign and domestic flying boats the characteristics of which are being obtained under similar test conditions in the N.A.C.A. tank. The take-off distance and time for a flying boat having the hull of the Calcutta are compared at two values of the gross load with the corresponding distances and times for the same flying boat having hulls of two representative American types, the Sikorsky S-40 and the N.A.C.A. 11-A. This comparison indicates that for hulls of the widely different forms compared, the differences in take-off time and distance are negligible.
    Type: NACA-TN-590
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  • 71
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    Stability of structural members under axial load (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The principles of the cross method of moment distribution are used to check the stability of structural members under axial load. A brief theoretical treatment of the subject, together with an illustrative problem, is included as well as a discussion of the reduced modulus at high stresses and a set of tables to aid in the solution of practical problems.
    Type: NACA-TN-617
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  • 72
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    Theoretical span loading and moments of tapered wings produced by aileron deflection (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of tapered ailerons on linearly tapered wings is theoretically determined. Four different aileron spans are considered for each of three wing aspect ratios and each of four wing taper ratios. The change in lift on one half of the wing, the rolling moment, the additional induced drag, and the yawing moment, due to aileron deflection, are represented by non dimensional coefficients. Similar coefficients are given for the damping and yawing moments, the additional drag, and the change in lift, due to rolling. It was found possible to effect a fairly close agreement between the theoretical and experimental rolling moments by introducing into the theoretical expression for the rolling moment an effective change in angle of attack obtained from an analysis of flap data. The theoretical curves show that the highly tapered wing with long ailerons has a lower ratio of yawing to rolling moment and a lower additional induced drag than wings with less taper.
    Type: NACA-TN-589
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  • 73
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    The Measurement of Air Speed in Airplanes (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Various methods of measuring the air speed of airplanes are described. Particular emphasis is placed on the procedure required to obtain precise measurements of speed by the use of the suspended Pitot-static head or the suspended static head. Typical calibration curves for service installations of Pitot-static heads are shown and the relation between errors in air speed and corresponding errors in observed altitude for such installations is discussed. There is included a brief discussion of various speed-course methods of measuring speed.
    Type: NACA-TN-616
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  • 74
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    Empirical corrections to the span load distribution at the tip (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis of existing pressure-distribution data was made to determine the variation of the tip loading with wing plan form. A series of empirical tip corrections was derived that may be added to theoretical curves in certain cases to obtain a closer approach to the actual loading at the tip. The analysis indicated that the need for a tip correction decreases as either the aspect ratio or the wing taper is increased. In general, it may be said that, for wings of conventional aspect ratio, corrections to the theoretical span load curves are necessary only if the wing is tapered less than 2:1 and has a blunt tip. If the tip is well rounded in plan form, no correction appears necessary even for a wing with no taper.
    Type: NACA-TN-606
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  • 75
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    Strain measurements on small duralumin box beams in bending (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Extensive strain-gage measurements were made chiefly on the tension side of five small rectangular box beams constructed of sheet duralumin. The main conclusion was that within the test range the tension cover may be considered as being fully effective but that at any given point on the beam there may be unaccountable variations of 5 percent from the calculated stresses on the thicker sheets tested (0.044 and 0.023 inch) and of 10 percent or more on the thinnest sheet tested (0.014 inch).
    Type: NACA-TN-588
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  • 76
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    Motion of the two-control airplane in rectilinear flight after initial disturbances with introduction of controls following an exponential law (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An airplane in steady rectilinear flight was assumed to experience an initial disturbance in rolling or yawing velocity. The equations of motion were solved to see if it was possible to hasten recovery of a stable airplane or to secure recovery of an unstable airplane by the application of a single lateral control following an exponential law. The sample computations indicate that, for initial disturbances complex in character, it would be difficult to secure correlation with any type of exponential control. The possibility is visualized that the two-control operation may seriously impair the ability to hasten recovery or counteract instability.
    Type: NACA-TN-615
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  • 77
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    Noise from Propellers with Symmetrical Sections at Zero Blade Angle (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theory has been deduced for the "rotation noise" from a propeller with blades of symmetrical section about the chord line and set at zero blade angle. Owing to the limitation of the theory, the equations give without appreciable error only the sound pressure for cases where the wave lengths are large compared with the blade lengths. With the aid of experimental data obtained from a two-blade arrangement, an empirical relation was introduced that permitted calculation of higher harmonics. The generality of the final relation given is indicated by the fundamental and second harmonic of a four-blade arrangement.
    Type: NACA-TN-605
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  • 78
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    Fuselage-drag tests in the variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5 (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are presented of the drag tests of six bodies of revolution with systematically varying shapes and with a fineness ratio of 5. The forms were derived from source-sink distributions, and formulas are presented for the calculation of the pressure distribution of the forms. The tests were made in the N.A.C.A. variable-density tunnel over a range of values of Reynolds number from about 1,500,000 to 25,000,000. The results show that the bodies with the sharper noses and tails have the lowest drag coefficients, even when the drag coefficients are based on the two-thirds power of the volume. The data shows the most important single characteristic of the body form to be the tail angle, which must be fine to obtain low drag.
    Type: NACA-TN-614
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  • 79
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    Full-scale Wind-tunnel and Flight Tests of a Fairchild 22 Airplane Equipped with External-airfoil Flaps (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel and flight tests have been made of a Fairchild 22 airplane equipped with a wing having external-airfoil flaps that also perform the function of ailerons. Lift, drag, and pitching-moment coefficients of the airplane with several flap settings, and the rolling- and yawing-moment coefficients with the flaps deflected as ailerons were measured in the full-scale tunnel with the horizontal tail surfaces and propeller removed. The effect of the flaps on the low speed and on the take-off and landing characteristics, the effectiveness of flaps when used as ailerons, and the forces required to operate them as ailerons were determined in flight. The wind-tunnel tests showed that the flaps increased the maximum lift coefficient of the airplane from 1.51 with the flap in the minimum drag position to 2.12 with the flap in the minimum drag position to 2.12 with the flap deflected 30 degrees. In the flight tests the minimum speed decreased from 46.8 miles per hour with the flaps up to 41.3 miles per hour with the flaps deflected. The required take-off run to attain a height of 50 feet was reduced from 820 to 750 feet and the landing run from a height of 50 feet was reduced from 930 to 480 feet. The flaps for this installation gave lateral control that was not entirely satisfactory. Their rolling action was good but the adverse yaw resulting from their use was greater than is considerable, and the stick forces required to operate them increased too rapidly with speed.
    Type: NACA-TN-604
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  • 80
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    The Effect of Curvature on the Transition from Laminar to Turbulent Boundary Layer (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the flow over the upper surface of a wing, a discrepancy between the predicted and actual point of transition from laminar to turbulent boundary layer was found. This effect may be due to the comparatively small radius of curvature of the upper surface of the wing. Tests were undertaken to investigate this effect. As far as the authors know, the present investigation is the first to show that curvature has a pronounced effect on the transition of the boundary layer from the laminar to the turbulent state. It appears that three important results have been obtained thus far. First, the experimental points for the convex and concave side of the sheet are consistent with each other and, with the experimental accuracy involved, lie on the same curve. Second, this curve can be approximated by a straight line. Third, the order of magnitude of the variation is such that the curvature ordinarily used on the upper surface of an airplane wing might double the critical Reynolds number.
    Type: NACA-TN-613
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  • 81
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    Heat transfer from cylinders having closely spaced fins (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The heat-transfer coefficients have been determined for five steel cylinders having fins 1.22 inches wide and the spacing between the fins ranging from 0.022 to 0.131 inch. The cylinders were tested with and without baffles in a wind tunnel; they were also tested enclosed in jackets with the cooling air supplied by a blower. A maximum heat transfer was reached at a fin space of about 0.45 inch for the cylinders tested with each of the three methods of cooling investigated. The rise in temperature of the air passing between the fins and the change in flow pattern were found to be important factors limiting the heat transfer that may be obtained by decreasing the fin space. The use of baffles for directing the air around the cylinders with closely spaced fins proved very effective in increasing the over-all heat-transfer coefficient, provided that the spacing was not appreciably less than that for maximum heat transfer.
    Type: NACA-TN-602
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  • 82
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    A Preliminary Study of Flame Propagation in a Spark-ignition Engine (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The N.A.C.A. combustion apparatus was altered to operate as a fuel-injection, spark-ignition engine, and a preliminary study was made of the combustion of gasoline-air mixtures at various air-fuel ratios. Air-fuel ratios ranging from 10 to 21.6 were investigated. Records from an optical indicator and films from a high-speed motion-picture camera were the chief sources of data. Schlieren photography was used for an additional study. The results show that the altered combustion apparatus has characteristics similar to those of a conventional spark-ignition engine and should be useful in studying phenomena in spark-ignition engines. The photographs show the flame front to be irregularly shaped rather than uniformly curved. With a theoretically correct mixture the reaction, as indicated by the photographs, is not completed in the flame front but continues for some time after the combustion front has traversed the mixture.
    Type: NACA-TN-603
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  • 83
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    The Lateral Instability of Deep Rectangular Beams (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimental and analytical studies were made of solid and hollow deep rectangular beams to study their lateral instability under various conditions of loading and restraint. The tests were made on bars and tubes of 17ST aluminum alloy. Failure by lateral buckling occurred only in tests on the solid beams. It was found that, within the elastic range, the test results were in agreement with the classical theory for the lateral buckling of deep beams as given by Prandtl, Mitchell, and Timoshenko. The tests were extended to the inelastic range, where it was found that the substitution for Young's modulus of an average modulus of elasticity derived from the stress-strain curve made it possible to predict instability at high stresses.
    Type: NACA-TN-601
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  • 84
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    Discharge characteristics of a double injection-valve single-pump injection system (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The discharge characteristics of two similar injection valves operated by a single-cylinder fuel-injection pump were determined with an apparatus that measured the quantity of fuel discharged from each valve during every 0.5 degrees of pump rotation. It was found that similar discharges took place from the two valves at all pump speeds when the valve-opening pressures, the nozzle-orifice diameters, and the injection-tube lengths were the same for both valves. Under these conditions, the effects of changing the pump speed, the pump throttle setting, or the nozzle orifice diameter were very similar to those occurring with a single-injection valve. By a proper selection of discharge-orifice areas and valve-opening pressures it was possible to obtain a great many combinations of discharge quantities, discharge rates, and injection timings for the two valves. A series of tests using injection tubes of unequal lengths for the two valves showed that under these conditions the injection timing and the fuel quantity discharged from each valve varies widely and erratically with changes in the pump speed.
    Type: NACA-TN-600
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  • 85
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    Charts expressing the time, velocity, and altitude relations for an airplane diving in a standard atmosphere (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report charts are given showing the relation between time, velocities, and altitude for airplanes having various terminal velocities diving in a standard atmosphere. The range of starting altitudes is from 8,000 to 32,000 feet, and the terminal velocities vary from 150 to 550 miles per hour. A comparison is made between an experimental case and the results obtained from the charts. Examples pointing out the use of the charts are included.
    Type: NACA-TN-599
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  • 86
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    Wind-tunnel tests of a Clark Y wing with 'Maxwell' leading-edge slots (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests of a Clark Y wing equipped with "Maxwell" type leading-edge slots were conducted in the N.A.C.A. 7- by 10-foot tunnel to ascertain the aerodynamic characteristics, which involved the determination of the best slot-gap opening, the effects of slat width, and the effect of a trailing-edge flap. The Maxwell wing with a wide-chord slat (0.30 c(sub w)) and with a 0.211 c(sub w) split flap deflected 60 degrees had a C(sub L sub max) of 2.53 or about twice that of the plain wing. The wing with the wide slat also had, in general, improved aerodynamic characteristics over those of the Maxwell wing with slat, and had about the same aerodynamic characteristics as a Handley Page slotted wing with approximately the same size of slat.
    Type: NACA-TN-598
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  • 87
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    Notes on the calculation of the minimum horizontal tail surface for airplanes equipped with wing flaps (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method of calculating the horizontal tail area for an airplane equipped with flaps is presented.. The general problem of tail design, the effects of flaps on the factors involved, and the manner in which the flaps change the requirements upon which the minimum horizontal tail area is based are discussed.
    Type: NACA-TN-597
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  • 88
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    Full-scale Wind-tunnel and Flight Test of a Fairchild 22 Airplane Equipped with a Zap Flap and Zap Ailerons (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wing equipped with a Zap flap and Zap ailerons was tested on a Fairchild 22 airplane in the full-scale wind tunnel and in flight to determine the effect of the flaps and ailerons on the performance and the control characteristics of the airplane. The flaps were 0.30 of the wing chord and 0.83 of the wing span. Two sets of ailerons having equal areas but different proportions were tested, one set being 0.56 of the semispan and 0.18 of the chord and the other set being 0.46 of the semispan and 0.22 of the chord. The wind-tunnel tests showed that, when the ailerons and horizontal tail surfaces were removed, the flaps increased the maximum lift coefficient from 1.48 to 2.39. In flight, the fully deflected flaps decreased the minimum speed from 48.2 to 38.8 miles per hour. The take-off and landing distances were both reduced by the flaps. The wind-tunnel tests showed the ailerons to increase the drag coefficient, at a lift coefficient and Reynolds Number corresponding to the high speed of the airplane, from 0.0432 to 0.0498 and 0.0514, the 0.46 semispan ailerons giving the highest drag. In the flight tests both sets of ailerons were found to give satisfactory rolling action in the normal-flight range. They required relatively large stick forces for their operation, however, and the variation of the forces with aileron deflection was not linear.
    Type: NACA-TN-596
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  • 89
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    Synthetic Resins in Aircraft Construction - Their Composition, Properties, Present State of Development and Application to Light Structures (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a brief review of the properties that have been attained with the synthetic materials with which we are at present familiar. Results of investigations are presented as well as possibilities for construction applications. Endurance strength and bonding tests are also presented.
    Type: NACA-TM-841
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  • 90
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    The stress distribution in shell bodies and wings as an equilibrium problem (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report treats the stress distribution in shell-shaped airplane components (fuselage, wings) as an equilibrium problem; it includes both cylindrical and non-cylindrical shells. In particular, it treats the stress distribution at the point of stress application and at cut-out points.
    Type: NACA-TM-817
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  • 91
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    Some experiments on the slipstream effect (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The models designated "Torino 30, 31, 32" are horizontal tail surfaces of rectangular, triangular, and elliptical plan form and all of the same profile section. Tests were carried out with the object being to determine the effect of the propeller slipstream on the aerodynamical characteristics of the horizontal stabilizer. The results presented correspond to a first series of tests made without an interposed wing and in which the distance between the plane of the propeller disk and the tail was maintained constant.
    Type: NACA-TM-820
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  • 92
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    Turbulent boundary layer of an airfoil (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A need has arisen for a new determination of the velocity profiles in the boundary layer. Assuming that the character of the velocity distribution depends to a large extent on the character of the shear distribution across the boundary layer, we shall consider the nature of the shear distribution for a boundary layer with a pressure gradient.
    Type: NACA-TM-822
    Format: application/pdf
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  • 93
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    Wing-Fuselage Interference Comparison of Conventional and Airfoil-Type-Fuselage Combinations (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-509
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  • 94
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    An analysis of the factors that determine the periodic twist of an autogiro rotor blade, with a comparison of predicted and measured results (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents an analysis of the factors that determine the periodic twist of a rotor blade under the action of the air forces on it. The results of the analysis show that the Fourier coefficients of the twist are linear expressions involving only the tip-speed ratio, the pitch setting, the inflow coefficient, the pitching-moment coefficient of the blade airfoil section, and the physical characteristics of the rotor blade and machine. The validity of the analysis was examined by using it to predict the twist of a rotor whose twist characteristics had previously been measured in flight. The agreement between the calculated and experimental results was satisfactory.
    Type: NACA-TR-600
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  • 95
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    An analytical and experimental study of the effect of periodic blade twist on the thrust, torque, and flapping motion of an autogiro rotor (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis is made of the influence on autogiro rotor characteristics of a periodic blade twist that varies with the azimuth position of the rotor blade and the results are compared with experimental data. The analysis expresses the influence of this type of twist upon the thrust, torque, and flapping motion of the rotor. The check against experimental data shows that the periodic twist has a pronounced influence on the flapping motion and that this influence is accurately predicted by the analysis. The influence of the twist upon the thrust and torque could be demonstrated only indirectly, but its importance is indicated.
    Type: NACA-TR-591
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  • 96
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    Blower Cooling of Finned Cylinders (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several electrically heated finned steel cylinders enclosed in jackets were cooled by air from a blower. The effect of the air conditions and fin dimensions on the average surface heat-transfer coefficient q and the power required to force the air around the cylinders were determined. Tests were conducted at air velocities between the fins from 10 to 130 miles per hour and at specific weights of the air varying from 0.046 to 0.074 pound per cubic foot. The fin dimensions of the cylinders covered a range in pitches from 0.057 to 0.25 inch average fin thicknesses from 0.035 to 0.04 inch, and fin widths from 0.67 to 1.22 inches.
    Type: NACA-TR-587
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  • 97
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    Fuel Spray and Flame Formation in a Compression-Ignition Engine Employing Air Flow (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of air flow on fuel spray and flame formation in a high-speed compression-ignition engine have been investigated by means of the NACA combustion apparatus. The process was studied by examining high-speed motion pictures taken at the rate of 2,200 frames a second. The combustion chamber was of the flat-disk type used in previous experiments with this apparatus. The air flow was produced by a rectangular displacer mounted on top of the engine piston. Three fuel-injection nozzles were tested: a 0.020-inch single-orifice nozzle, a 6-orifice nozzle, and a slit nozzle. The air velocity within the combustion chamber was estimated to reach a value of 425 feet a second. The results show that in no case was the form of the fuel spray completely destroyed by the air jet although in some cases the direction of the spray was changed and the spray envelope was carried away by the moving air. The distribution of the fuel in the combustion chamber of a compression-ignition engine can be regulated to some extent by the design of the combustion chamber, by the design of the fuel-injection nozzle, and by the use of air flow.
    Type: NACA-TR-588
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  • 98
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    Annual report of the National Advisory Committee for Aeronautics (23rd).administrative report including Technical Report nos. 577 to 611 (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
    Type: NACA-AR-23
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  • 99
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    Wind-tunnel investigation of ordinary and split flaps on airfoils of different profile (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of wind tunnel tests of the Clark Y, the NACA 23012 and the NACA 23021 airfoils equipped with full-span ordinary flaps and with full-span simple split flaps. The principal object of the tests was to determine the characteristics of the airfoils with ordinary flaps and in addition, to determine the relative merits of the various airfoils when equipped with either ordinary flaps or with simple split flaps. The Clark Y airfoil was tested with 3 widths of ordinary flap, 10, 20, and 30 percent of the airfoil chord. The optimum width of the ordinary and the simple split flap based on the maximum lift attained with the Clark Y airfoil was then tested on each of the other two airfoils.
    Type: NACA-TR-554
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  • 100
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    THE DESIGN OF AIRPLANE-ENGINE SUPERCHARGERS (1937)
    In:  CASI
    Details
    Publication Date: 2019-05-10
    Keywords: PROPELLANTS
    Type: NACA-TM-839
    Format: application/pdf
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