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  • 1
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    On focal points of SKS (1938)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 28, no. 6, pp. 197-200, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Velocity of soundwaves from gun-fire in Southern California (1938)
    In:  Trans., Am. Geophys. Union, Milano, Gustav Fischer, vol. 19, no. 6, pp. 156, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Velocity analysis ; Applied geophysics ; NOISE ; Acoustics ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Observed times of the Montana earthquake, 1935 (1938)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 28, no. 6, pp. 85-88, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Seismology ; Earthquake ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Depth and geographical distribution of deep-focus earthquakes (1938)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 49, no. 6, pp. 249-288, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Seismology ; Seismicity ; Hypocentral depth
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Seismic waves in the core of the earth (1938)
    In:  Nature, Milano, Gustav Fischer, vol. 141, no. 6, pp. 371, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Waves ; Seismology ; earth Core
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    P' and the earth's core (1938)
    In:  Month. Notices Royal astr. Soc., Geophys. Suppl., Milano, Gustav Fischer, vol. 4, no. 6, pp. 363-372, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Waves ; earth Core ; P-waves ; Diffraction
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Report of the Interdivisional Committee on Borderland Fields Between Geology, Physics, and Chemistry, 1937 (1938)
    Nat. Research Council, Div. Geology and Geography
    In:  London, Nat. Research Council, Div. Geology and Geography, vol. 159, no. 22, pp. 662-664, (ISBN 0-470-87000-1 (HB), ISBN 0-470-87001-X (PB))
    Details
    Publication Date: 1938
    Keywords: Project report/description ; Geol. aspects
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Witterungsverlauf und Ernteertrag in der Kurmark bei den Hauptgetreidearten und Kartoffeln. (1938)
    In:  Landwirtschaftl. Jahrbuch 86:823-924.
    Details
    Publication Date: 1938
    Description: Erarbeitung einer ausbaufähigen Methode für das Erfassen des Witterungsablaufes; Vergleichen einer Zwölfjahresreihe von Erträgen mit dem Witterungsablauf; bearbeitet wurden Winterroggen, Winterweizen, Wintergerste, Hafer, Sommergerste, Sommerweizen, Kartoffeln KATASTER-BESCHREIBUNG: Zusammenhang Witterung und Ertrag bei Getreide und Kartoffeln KATASTER-DETAIL: Delta Wasserversorgung (Frühjahr) - und Delta Wasserversorgung (Mai, Juni, Juli) +, dann Ertrag (Getreide) +; Delta T (frühe Entwicklungsstadien) -, dann Ertrag (Winterroggen, Hafer) +; Delta T (April) -, dann Ertrag (Hafer) +; Delta Nied (April, Mai) -, dann Ertrag (Winterweizen) +; delta T (Mai) -, dann Ertrag (Winterroggen) +; Delta T +, dann Ertrag (Kartoffel) +; Delta Nied (Juli, August) +, dann Ertrag (Kartoffel) +;
    Keywords: Brandenburg ; 1924-37 ; Kartoffeln ; Ertrag ; Getreide ; Witterung
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    BIBLIOGRAPHY INKA BB
  • 9
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    Grundzüge der Bioklimatik des Menschen (1938)
    In:  Klima - Wetter - Mensch, Woltereck, H. (Hrsg.), Verlag von Quelle und Meyer, Lepzig, S.127-229
    Details
    Publication Date: 1938
    Description: Bioklimatik einzelner Klimaelemente, atmosphärischer Zustände und Vorgänge KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Umweltmedizin
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    BIBLIOGRAPHY INKA BB
  • 10
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    Grundriss einer Meteorobiologie (1938)
    In:  Verlag von Julius Springer, Berlin
    Details
    Publication Date: 1938
    Description: Meteorotrope Krankheiten, Saisonkrankheiten KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Umweltmedizin
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    BIBLIOGRAPHY INKA BB
  • 11
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    Klima und Krankheitserreger (1938)
    In:  Klima - Wetter - Mensch, Woltereck, H. (Hrsg.), Verlag von Quelle und Meyer, Lepzig, S.253-296
    Details
    Publication Date: 1938
    Description: Seuchenerreger und -überträger und der Einfluss von Temperatur, Feuchtigkeit und Jahresschwankungen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Umweltmedizin
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    BIBLIOGRAPHY INKA BB
  • 12
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    Geologie des Niederrheinisch-Westfälischen Steinkohlengebirges (1938)
    Springer Verlag
    In:  Berlin, Springer Verlag, vol. 1, no. 22, pp. 65-70, (ISBN 3-7643-0253-4)
    Details
    Publication Date: 1938
    Keywords: Geol. aspects ; Mining geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Determination of Venus winds by ground-based radio tracking of the VEGA balloons (1938)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A global array of 20 radio observatories was used to measure the three-dimensional position and velocity of the two meteorological balloons that were injected into the equatorial region of the Venus atmosphere near Venus midnight by the VEGA spacecraft on June 11 and 15, 1985. Initial analysis of only radial velocities indicates that each balloon was blown westward about 11,500 kilometers (8,000 kilometers on the night side) by zonal winds with a mean speed of about 70 meters per second. Excursions of the data from a model of constant zonal velocity were generally less than 3 meters per second; however, a much larger variation was evident near the end of the flight of the second balloon. Consistent systematic trends in the residuals for both balloons indicate the possibility of a solar-fixed atmospheric feature. Rapid variations in balloon velocity were often detected within a single transmission (330 seconds); however, they may represent not only atmospheric motions but also self-induced aerodynamic motions of the balloon.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Science (ISSN 0036-8075); 231; 1414-141
    Format: text
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  • 14
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    Two-dimensional subsonic compressible flow past elliptic cylinders (1938)
    In:  CASI
    Details
    Publication Date: 2019-05-31
    Keywords: unknown
    Type: REPT.-624
    Format: text
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  • 15
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    Some Investigations of the General Instability of Stiffened Metal Cylinders V : Stiffened Metal Cylinders Subjected to Pure Bending (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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 pure bending at the C.I.T. This part of the investigation included tests of 46 sheet-covered specimens. The most significant result was the determination of a new design parameter for the case of a stiffened metal cylinder subjected to pure bending.
    Type: NACA-TN-909
    Format: application/pdf
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  • 16
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    Stresses in reinforcing rings due to axial forces in cylindrical and conical stressed skins (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: At the ends of a monocoque fuselage concentrated axial forces in the skin must generally be taken up. Such axial forces must also be taken up in the case of other members where axial forces from the neighboring stressed skin construction must be considered. In order to take up these axial forces two bulkheads or reinforcing frames may be arranged at the positions where the forces are applied. If these bulkheads are in the form of rings, bending moments are set up in them. In the present paper computations are performed for obtaining the value of these bending moments.
    Type: NACA-TM-847
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  • 17
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    Load Tests on a Stiffened Circular Cylindrical Shell (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report describes tests in which the stress distribution may be determined in a stiffened circular cylindrical shell loaded longitudinally at four symmetrically situated points. As being of particular importance are the cases investigated of groups of bending and arching or convexing forces, respectively. From the stress measurements on the longitudinal stiffeners, the shear stresses and the bulkhead ring stresses in the skin could be evaluated. These measurements showed that the "simple shear field" used in theoretical computations in which all normal stresses in the skin are neglected, must be extended by the addition of the transverse or circumferential stresses if the bulkhead rings are not riveted to the skin.
    Type: NACA-TM-864
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  • 18
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    Behavior of Static Pressure Heads at High Speeds (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These tests proved the practicability of static pressure heads at speeds up to 400 km/h (248.5 mph). It weighs 6.5 kg or 2.5 times as much as the old head. The position of the pressure head below the airplane was determined by bearing method at different speeds and for different lengths of suspension. It was established that for the measured speed range a 20 to 24 meter suspension length was sufficient to assure a minimum distance of 6 meters from the airplane without introducing any appreciable errors in the results due to wrong static pressure.
    Type: NACA-TM-865
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  • 19
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    Wind-tunnel Investigations on Flexural-torsional Wing Flutter (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For the purpose of testing the theory of an oscillating airfoil of two degrees of freedom, a wing was mounted in the wind tunnel between two walls in such a manner that it could execute vertical (flexural) oscillations as well as torsional oscillations about an arbitrary axis parallel to the span. It was possible to vary the inertia and elasticity parameters and also to increase artificially the negligibly small natural damping of the system. The oscillations were recorded to a strongly magnified scale. The experimentally determined critical (or flutter) velocities fully agree with the theoretical ones of Wagner and Kussner within the limits of computational and measuring accuracy. An extremely narrow wing without end walls (three dimensional problem) showed the same oscillations as one with end walls (two-dimensional problem).
    Type: NACA-TM-877
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  • 20
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    Aerodynamic Characteristics of a 4-engine Monoplane Showing Effects of Enclosing the Engines in the Wing and Comparisons of Tractor- and Pusher-propeller Arrangements (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-456
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  • 21
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    A study of the torque equilibrium of an autogiro rotor (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two improvements have been made in the method developed in NACA Reports nos. 487 and 591 for the estimation of the inflow velocity required to overcome a given decelerating torque in an autogiro rotor. At low tip-speed ratios, where the assumptions necessary for the analytical integrations of the earlier papers are valid, the expressions therein derived are greatly simplified by combining and eliminating terms with a view of minimizing the numerical computations required. At high tip-speed ratios, by means of charts based on graphical integrations, errors inherent in the assumptions associated with the analytical method are largely eliminated. The suggested method of estimating the inflow velocity presupposes a knowledge of the decelerating torque acting on the rotor; all available full-scale experimental information on this subject is included.
    Type: NACA-TR-623
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  • 22
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    A discussion of certain problems connected with the design of hulls of flying boats and the use of general test data (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a survey of problems encountered in applying general test data to the design of flying-boat hulls. It is shown how basic design features may be readily determined from special plots of test data. A study of the effect of the size of a flying boat on the probable limits to be covered by the general test data is included and recommendations for special tests and new methods of presenting test data for direct use in design are given.
    Type: NACA-TR-625
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  • 23
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    A theory for primary failure of straight centrally loaded columns (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theory of primary failure of straight centrally loaded columns is presented. It is assumed that the column cross section and the load are constant throughout the length.
    Type: NACA-TR-582
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  • 24
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    A study of the two-control operation of an airplane (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The two-control operation of a conventional airplane is treated by means of the theory of disturbed motions. The consequences of this method of control are studied with regard to the stability of the airplane in its unconstrained components of motion and the movements set up during turn maneuvers.
    Type: NACA-TR-579
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  • 25
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    Prechamber Compression-Ignition Engine Performance (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Single-cylinder compression-ignition engine tests were made to investigate the performance characteristics of prechamber type of cylinder head. Certain fundamental variables influencing engine performance -- clearance distribution, size, shape, and direction of the passage connecting the cylinder and prechamber, shape of prechamber, cylinder clearance, compression ratio, and boosting -- were independently tested. Results of motoring and of power tests, including several typical indicator cards, are presented.
    Type: NACA-TR-577
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  • 26
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    Interference of Wing and Fuselage from Tests of the 18 Combinations in the N.A.C.A. Variable-density Tunnel - Combination with Split Flaps (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of the wing-fuselage interference investigation in progress in the N.A.C.A. variable density wind tunnel, the effects of various split-flap arrangements applied to wing-fuselage combinations were determined. Split flaps were found to exert their influence independently of the interference, and their effects on the aerodynamic characteristics of rectangular-airfoil combinations appeared to be more or less proportional to their exposed span lengths. The interference, moreover, showed the same character with the split flaps as without them.
    Type: NACA-TN-640
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  • 27
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    Tests of a Contra-propeller for Aircraft (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests of an 8-blade contra-propeller of 32-inch diameter in combination with a 4-inch, 36-inch diameter adjustable pitch, metal propeller at pitch setting of 15, 25, 35, and 45 degrees at 0.75 R were made. The tests showed a significant increase in effective thrust of the combination over that of the propeller alone for value V/nD somewhat below those for maximum efficiency and without a corresponding increase of power absorbed. From 1/2 percent to 2-1/2 percent in propulsive efficiency was thus gained in this range. In all but one case, however, the peak propulsive efficiency of the combination was found to be from 1 to 2 percent less than that of the propeller alone. Counter torque on the contra-propeller amounted to about 50 percent of the propeller torque.
    Type: NACA-TN-677
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  • 28
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    A preliminary investigation of boundary-layer transition along a flat plate with adverse pressure gradient (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Boundary-layer surveys were made throughout the transition region along a smooth flat plate placed in an airstream of practically zero turbulence and with an adverse pressure gradient. The boundary-layer Reynolds number at the laminar separation point was varied from 1,800 to 2,600. The test data, when considered in the light of certain theoretical deductions, indicated that transition probably began with separation of the laminar boundary layer. The extent of the transition region, defined as the distance from a calculated laminar separation point to the position of the first fully developed turbulent boundary-layer profile, could be expressed as a constant Reynolds number run of approximately 70,000. Some speculations are presented concerning the application of the foregoing concepts, after certain assumptions have been made, to the problem of the connection between transition on the upper surface of an airfoil at high angles of attack and the maximum lift.
    Type: NACA-TN-639
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  • 29
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    Discharge characteristics of a simulated unit injection system (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Rate-of-discharge curves that show the discharge characteristics of an injection system having a very short fuel passage are presented. The rate of discharge closely follows the rate of displacement of the injection-pump plunger for open nozzles in which the maximum calculated pressures at the orifice do not exceed a certain value, which is dependent on the particular injection pump. With small orifices and high pump speeds, the rate of discharge does not follow the rate of plunger displacement because the higher discharge pressure results in increased leakage with corresponding decrease in discharge rate. The rate of discharge is not directly related to the rate of plunger displacement with automatic injection valves having closed nozzles. The types of pump check valve tested did not control the rate of cut-off or the discharge rate but they did affect the injection lag. Use of the short fuel passage eliminated the formation of secondary discharges.
    Type: NACA-TN-676
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  • 30
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    Tank Tests of Model 36 Flying Boat Hull (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: N.A.C.A. Model 36, a hull form with parallel middle body for half the length of the forebody and designed particularly for use with stub wings, was tested according to the general fixed-trim method over the range of practical loads, trims, and speeds. It was also tested free to trim with the center of gravity at two different positions. The results are given in the form of nondimensional coefficients. The resistance at the hump was exceptionally low but, at high planing speeds, afterbody interference made the performance only mediocre.
    Type: NACA-TN-638
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  • 31
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    Scavenging a Piston-ported Two-stroke Cylinder (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made with a specially designed engine to determine the scavenging characteristics of a large number of inlet-port shapes and arrangements and the optimum port arrangement and timing for this particular type of engine. A special cylinder construction permitted wide variations in timing for this particular type of engine. A special cylinder construction permitted wide variations in timing as well as in shape and arrangement of both the inlet and exhaust ports. The study of the effect of port shape combinations and timings on engine performance was made using illuminating gas as a fuel. Through variations in inlet-port arrangement and port timings, the value of the scavenging efficiency was increased from an original 44 percent to approximately 67 percent with a corresponding increase in power. With the optimum port arrangement and timing determined, a large number of performance runs were made under both spark-ignition and compression-ignition operation.
    Type: NACA-TN-674
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  • 32
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    The Pressure Available for Ground Cooling in Front of the Cowling of Air-cooled Airplane Engines (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made of the factors affecting the pressure available for ground cooling in front of a cowling. Most of the results presented were obtained with a set-up that was about one-third full scale. A number of isolated tests on four full-scale airplanes were made to determine the general applicability of the model results. The full-scale tests indicated that the model results may be applied qualitatively to full-scale design and quantitatively as a first approximation of the front pressure available for ground cooling.
    Type: NACA-TN-673
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  • 33
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    Flow Observations with Tufts and Lampblack of the Stalling of Four Typical Airfoil Sections in the NACA Variable-density Tunnel (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A preliminary investigation of the stalling processes of four typical airfoil sections was made over the critical range of the Reynolds Number. Motion pictures were taken of the movements of small silk tufts on the airfoil surface as the angle of attack increased through a range of angles including the stall. The boundary-layer flow also at certain angles of attack was indicated by the patterns formed by a suspension of lampblack in oil brushed onto the airfoil surface. These observations were analyzed together with corresponding force-test measurements to derive a picture of the stalling processes of airfoils.
    Type: NACA-TN-672
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  • 34
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    A method of rapidly estimating the position of the laminar separation point (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method is described of rapidly estimating the position of the laminar separation point from the given pressure distribution along a body; the method is applicable to a fairly wide variety of cases. The laminar separation point is found by the von Karman-Millikan method for a series of velocity distributions along a flat plate, which consist of a region of uniform velocity followed by a region of uniform decreased velocity. It is shown that such a velocity distribution can frequently replace the actual velocity distribution along a body insofar as the effects on laminar separation are concerned. An example of the application of the method is given by using it to calculate the position of the laminar separation point on the NACA 0012 airfoil section at zero lift. The agreement between the position of the separation point calculated according to the present method and that found from more elaborate computations is very good.
    Type: NACA-TN-671
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  • 35
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    The estimation of the rate of change of yawing moment with sideslip (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel data are presented on the rate of change of yawing moment with sideslip for tests of 9 complete airplane models, 20 fuselage shapes, and 3 wing models with various combinations of dihedral, sweepback, and twist. The data were collected during a survey of existing information, which was made to find a reliable method of computing the yawing moment due to sideslip. Important errors common to methods of computation used at present appear to be due to large interference effects, the investigation of which will undoubtedly require an extensive program of systematic wind-tunnel tests. At present it is necessary to place considerable reliance on past design experience in proportioning an airplane so as to obtain a reasonable degree of directional stability.
    Type: NACA-TN-636
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  • 36
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    NACA Stall-Warning Indicator (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stall-warning indicator employs a total-head tube located close to the wing surface in a region wherein local stalling occurs before the main portion of the wing stalls. The artificial production of a localized stalled region is accomplished by means of a sharp leading edge extending a few inches along the span. An abrupt drop in the total pressure relative to a static reference taken at some convenient point occurs at the stall in this region. Thin drop in total pressure caused the contraction of a pressure cell to which the total-head tube and the static orifice are connected and closed an electrical circuit that actuates a warning signal.
    Type: NACA-TN-670
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  • 37
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    The drag of inflatable rubber de-icers (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Force tests on rubber de-icer models of several different profiles, at approximately one-third full scale, been carried out in the NACA 8-foot high speed wind tunnel. The conventional de-icer installation, deflated, added about 15 percent to the smooth-wing drag and, inflated, added about 100 percent. An improved installation with flash attaching strips added about 10 percent, deflated. The bulging, or ballooning, of de-icers from the wing surface is described and some remedies are discussed.
    Type: NACA-TN-669
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  • 38
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    Tank Tests of a Model of One Hull of the Savoia S-55-X Flying Boat N.A.C.A. Model 46 (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A model of one of the twin hulls of the Italian Savoia S-55-X flying boat (N.A.C.A. Model 46) was tested in the N.A.C.A. tank according to the general method. The data obtained from these tests cover a broad range of speeds, loads, and trims and are given in nondimensional form to facilitate their use in applying this form of hull to any other flying boat or comparing it's performance with the performance of any other hulls. The results show that the resistance characteristics at best trim of this model are excellent throughout the speed range. In order to compare the performance of the S-55-X hull with that of the 35, a pointed-step hull developed at the N.A.C.A. tank, the data are used in the computations of take-off example of a twin-hull, 23,500-pound flying boat. The calculations show that the S-55-X hull has better take-off performance.
    Type: NACA-TN-635
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  • 39
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    Hydrodynamic and Aerodynamic Tests of Models of Flying-boat Hulls Designed Flow Aerodynamic Drag - NACA Models 74, 74-A, and 75 (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present tests illustrate how the aerodynamic drag of a flying boat hull may be reduced by following closely the form of a low drag aerodynamic body and the manner in which the extent of the aerodynamic refinement is limited by poorer hydrodynamic performance. This limit is not sharply defined but is first evidenced by an abnormal flow of water over certain parts of the form accompanied by a sharp increase in resistance. In the case of models 74-A and 75, the resistance (sticking) occurs only at certain combinations of speed, load, and trim and can be avoided by proper control of the trim at high water speeds. Model 75 has higher water resistance at very high speeds than does model 74-A. With constant speed propellers and high takeoff speeds, it appears that the form of model 75 would give slightly better takeoff performance. Model 74-A, however, has lower aerodynamic drag than does model 75 for the same volume of hull.
    Type: NACA-TN-668
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  • 40
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    Operational treatment of the nonuniform-lift theory in airplane dynamics (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The method of operators is used in the application of nonuniform-lift theory to problems of airplane dynamics. The method is adapted to the determination of the lift under prescribed conditions of motion or to the determination of the motions with prescribed disturbing forces.
    Type: NACA-TN-667
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  • 41
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    Longitudinal stability in relation to the use of an automatic pilot (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of restraint in pitching introduced by an automatic pilot upon the longitudinal stability of an airplane has been studied. Customary simplifying assumptions have been made in setting down the equations of motion, and the results of computations based on the simplified equations are presented to show the effect of an automatic pilot installed in an airplane of known dimensions and characteristics. The equations developed have been applied by making calculations for a Clark biplane and a Fairchild 22 monoplane.
    Type: NACA-TN-666
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  • 42
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    The N.A.C.A. Optical Engine Indicator (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An optically recording engine-pressure indicator of simple and rugged construction has been developed for use in high-pressure and high temperature combustion research. This instrument is of the diaphragm type and has a natural frequency of about 10,000 cycles per second.
    Type: NACA-TN-634
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  • 43
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    Tests of N-85, N-86 and N-87 airfoil sections in the 11-inch high speed wind tunnel (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Three airfoils, the N-85, the N-86, and the N-87, were tested at the request of the Bureau of Aeronautics, Navy Department, to determine the suitability of these sections for use as propeller-blade sections. Further tests of the NACA 0009-64 airfoil were also made to measure the aerodynamic effect of thickening the trailing edge in accordance with current propeller practice. The N-86 and the N-87 airfoils appear to be nearly equivalent aerodynamically and both are superior to the N-85 airfoil. Comparison of those airfoils with the previously developed NACA 2409-34 airfoils indicate that the NACA 2409-34 is superior, particularly at high speeds. Thickening the trailing edge appears to have a detrimental effect, although the effect may be small if the trailing-edge radius is less than 0.5 percent of the cord. The N-86 and the N-87 airfoils appear to be nearly equivalent.
    Type: NACA-TN-665
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  • 44
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    Free-spinning Wind-tunnel Tests of a Low-wing Monoplane with Systematic Changes in Wings and Tails III : Mass Distributed Along the Wings (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-664
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  • 45
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    The effects of partial-span plain flaps on the aerodynamic characteristics of a rectangular and a tapered Clark Y wing (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine the aerodynamic characteristics of tapered and rectangular wings with partial-span plain flaps. Two Clark Y airfoils equipped with center section and with tip-section flaps were tested. The results showed that the aerodynamic characteristics of partial-span plain flaps were, in general, similar to those of split flaps of the same span, but that the lift and the drag were less for the wing with plain flaps than for the wing with split flaps of comparable size. For the rectangular wing with center-section plain flaps, the maximum lift and the lift-drag ratio at maximum lift were greater and the drag at maximum lift was less than for the wing with tip-section plain flaps of the same size. The maximum lift of the tapered wing varied in the same manner as that of the rectangular wing but the drag and the lift-drag-ratio relationship were opposite.
    Type: NACA-TN-663
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  • 46
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    Spinning Characteristics of Wings V : N.A.C.A. 0009, 23018, and 6718 Monoplane Wings (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Three rectangular monoplane wings having rounded tips were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The airfoil sections used were the N.A.C.A. 0009, 23018, and 6718. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. There is included an estimate of the yawing moment that must be furnished by parts of the airplane to balance the inertia couples and wing yawing moments for spinning equilibrium. The predicted angles of sideslip and yawing moments required for spinning equilibrium for a Clark Y wing with the same form are included for comparison.
    Type: NACA-TN-633
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  • 47
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    Gyroscopic Instruments for Instrument Flying (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The gyroscopic instruments commonly used in instrument flying in the United States are the turn indicator, the directional gyro, the gyromagnetic compass, the gyroscopic horizon, and the automatic pilot. These instruments are described. Performance data and the method of testing in the laboratory are given for the turn indicator, the directional gyro, and the gyroscopic horizon. Apparatus for driving the instruments is discussed.
    Type: NACA-TN-662
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  • 48
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    Improvement of aileron effectiveness by the prevention of air leakage through the hinge gap as determined in flight (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight investigation was made of the increase in effectiveness of ailerons that can be obtained by preventing flow of air through the wing at the hinges and of the possibility of reducing the aileron operating force by replacing ailerons having normal open hinge gaps with narrower but equally effective ailerons having sealed hinge gaps. Tests were made with a Fairchild 22 airplane with two sizes of plain unbalanced ailerons, one set having a chord equal to 0.18c, and the other chord equal to 0.09c. The results of the investigation show that improvement of the lateral-control effectiveness is obtained by completely preventing the flow of air through the wing at the hinge axis of conventional ailerons. The magnitude of the improvement depends on the aileron chord. For the 0.18c ailerons the gain in aileron effectiveness due to sealing the gap at the hinge axis was of the order of one-fifth and for the 0.09c ailerons the gain was about one-third. The importance of sealing the gap was demonstrated by the fact that the 0.09c ailerons with a slight increase in deflection range were made as effective as the 0.18c ailerons with an unsealed gap but required only about one-third as large an operating force.
    Type: NACA-TN-632
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  • 49
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    Wind-tunnel investigation of rectangular and tapered NACA 23012 wings with plain ailerons and full-span split flaps (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine the aerodynamic properties of rectangular and tapered NACA 23012 wings with plain ailerons and a full-span split flap, the flap retracting ahead of the ailerons. Measurements were made of lift and drag and of pitching, rolling, yawing, and hinge moments for all conditions of full-span flaps neutral and deflected at different chord locations. The results of the tests showed that a 0.20c(sub w) full span split flap located at approximately the 0.75c(sub w) point gave higher lift coefficients than had previously been obtained with a conventional 0.20c(sub w) partial-span split flap of a length to permit satisfactory control with plain ailerons. Still higher lifts were obtained if the full-span flap, when deflected, was moved back to the aileron axis. Moving the flap back to the aileron, in general, improved the aileron characteristics over those with the flap retracted. The most promising arrangement of full-span split flap and plain aileron combination tested, both for high lift and lateral control, was the rectangular wing with 0.20c(sub w) deflected 60 degrees at the 0.90c(sub w) location with 0.10c(sub w) semispan ailerons.
    Type: NACA-TN-661
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  • 50
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    Fatigue Testing of Wing Beam by the Resonance Method (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preliminary fatigue tests on two aluminum-alloy wing-beam specimens subjected to reversed axial loading are described. The motion used consists in incorporating one or two reciprocating motors in a resonance system of which the specimen is the spring element. A description is given of the reciprocating motors, and of the method of assembling and adjusting the vibrating system. The results indicate that the method is well adapted to fatigue tests of not only uniform wing beams but also wing beams with asymmetrical local reinforcements.
    Type: NACA-TN-660
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  • 51
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    Wind-tunnel Tests of Carburetor-intake Rams (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the NACA 20-foot wind tunnel of the ramming effect of three general types of carburetor intake rams for radial engines, namely, the internal constant area type, the external constant area type, and the external expanding type. The rams were installed on a radial air- cooled engine nacelle, and tests were made with and without the propeller operating. The results indicated that the external types having entrances near the front of the engine cowling gave the greatest ramming effect. The propeller increased the ramming effect for the external types. From considerations of the ramming effect, the best entrance location for the external types was close to the nose of the engine cowling. For the internal type, the best location was in a plane perpendicular to the propeller shaft and immediately forward of the engine cylinders.
    Type: NACA-TN-631
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  • 52
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    Wind-tunnel of three lateral-control devices in combination with a full-span slotted flap on an NACA 23012 airfoil (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section, and two-dimensional flow was approximated. The model was fitted with a full-span slotted flap having a chord 25.66 percent of the airfoil chord. The ailerons investigated extended over the entire span and each had a chord 10 percent of the airfoil chord. The types of ailerons tested were: retractable ailerons, slot-lip ailerons using the lip of the slot for ailerons, and plain ailerons on the trailing edge of the slotted flap. The data are presented in the form of curves of section lift, drag, and pitching-moment coefficients for the airfoil with flap deflected but with ailerons neutral, and of rolling-moment, yawing-moment, and hinge-moment coefficients calculated for a rectangular wing of aspect ratio 6 with a semi-span aileron and a full-span flap. For the ailerons investigated the data indicate that, from considerations of rolling and yawing moments produced and of stick forces desired, the retractable aileron is the most satisfactory means of lateral control for use with a full-span slotted flap.
    Type: NACA-TN-659
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  • 53
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    The Aerodynamic Drag of Five Models of Side Floats N.A.C.A. Models 51-E, 51-F, 51-G, 51-H, 51-J (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drag of five models of side floats was measured in the N.A.C.A. 7- by 10-foot wind tunnel. The most promising method of reducing the drag of floats indicated by these tests is lowering the angle at which the floats are rigged. The addition of a step to a float does not always increase the drag in the flying range, floats with steps sometimes having lower drag than similar floats without steps. Making the bow chine no higher than necessary might result in a reduction in air drag because of the lower angle of pitch of the chines. Since side floats are used formally to obtain lateral stability when the seaplane is operating on the water at slow speeds or at rest, greater consideration can be given to factors affecting aerodynamic drag than is possible for other types of floats and hulls.
    Type: NACA-TN-680
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  • 54
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    A general tank test of a model of the hull of the Pem-1 flying boat including a special working chart for the determination of hull performance (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of a general tank test of a 1/6 full-size model of the hull of the Pem-1 flying boat (N.A.C.A. model 18) are given in non-dimensional form. In addition to the usual curves, the results are presented in a new form that makes it possible to apply them more conveniently than in the forms previously used. The resistance was compared with that of N.A.C.A. models 11-C and 26(Sikorsky S-40) and was found to be generally less than the resistance of either.
    Type: NACA-TN-681
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  • 55
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    Generalized analysis of experimental observations in problems of elastic stability (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A generalized method of analyzing experimental observations in problems of elastic stability is presented in which the initial readings of load and deflection may be taken at any load less the critical load. The analysis is an extension of a method published by Southwell in 1932, in which it was assumed that the initial readings are taken at zero load.
    Type: NACA-TN-658
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  • 56
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    Tank Tests to Show the Effect Rivet Heads on the Water Performance of a Seaplane-Float (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 1/3.5 full-sized model of a seaplane float constructed from lines supplied by the Bureau of Aeronautics, Navy Department, was tested first with smooth painted bottom surfaces and then with round-head rivets, plate laps, and keel plates fitted to simulate the actual bottom of a metal float. A percentage increase in water resistance caused by the added roughness was found to be from 5 to 20 percent at the hump speed and from 15 to 40 percent at high speeds. The effect of the roughness of the afterbody was found to be negligible except at high trims. The model data were extrapolated to full size by the usual method that assumes the forces to vary according to Froude's law and, in the case of the smooth model, by a method of separation that takes into account the effect of scale on the frictional resistance. It was concluded that the effect of rivet heads on the take-off performance of a relatively high-powered float seaplane is of little consequence, but it may be of greater importance in the case of more moderately powered flying boats.
    Type: NACA-TN-657
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  • 57
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    Noise from propellers with symmetrical sections at zero blade angle, II (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In a previous paper (Technical Note No. 605), a theory was developed that required an empirical relation to calculate sound pressures for the higher harmonics. Further investigation indicated that the modified theory agrees with experiment and that the empirical relation was due to an interference phenomenon peculiar to the test arrangement used. Comparison is made between the test results for a two-blade arrangement and the theory. The comparison is made for sound pressures in the plane of the revolving blades for varying values of tip velocity. Comparison is also made at constant tip velocity for all values of azimuth angle B. A further check is made between the theory and the experimental results for the fundamental of a four-blade arrangement with blades of the same dimensions as those used in the two-blade arrangement.
    Type: NACA-TN-679
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  • 58
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    Principles involved in the cooling of a finned and baffled cylinder (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis of the cooling problems for a finned cylinder is made on the basis of the known fundamental principles of heat transfer from pipes. Experimental results that support the analysis are presented. The results of previous investigations on the problem are evaluated on the basis of the analysis and the results. An illustration of the application of these principles to a specific problem is included.
    Type: NACA-TN-655
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  • 59
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    Hydrodynamic and Aerodynamic Tests of Models of Floats for Single-float Seaplanes NACA Models 41-D, 41-E, 61-A, 73, and 73-A (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made in the NACA tank and in the NACA 7 by 10 foot wind tunnel on two models of transverse step floats and three models of pointed step floats considered to be suitable for use with single float seaplanes. The object of the program was the reduction of water resistance and spray of single float seaplanes without reducing the angle of dead rise believed to be necessary for the satisfactory absorption of the shock loads. The results indicated that all the models have less resistance and spray than the model of the Mark V float and that the pointed step floats are somewhat superior to the transverse step floats in these respects. Models 41-D, 61-A, and 73 were tested by the general method over a wide range of loads and speeds. The results are presented in the form of curves and charts for use in design calculations.
    Type: NACA-TN-656
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  • 60
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    Fuel Consumption of a Carburetor Engine at Various Speeds and Torques (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to obtain fuel-consumption curves for a single-cylinder engine with a Wright 1820-G and Pratt & Whitney 1340-H cylinder at varying speeds, manifold pressures, and air-fuel ratios. The 1340- H cylinder was tested at speeds from 1,200 to 2,400 r.p.m. and at manifold pressures from 21 to 38 inches of mercury absolute. Less than extensive tests were made of the 1820-G cylinder. The results of the tests showed that the minimum brake fuel consumption was obtained when the engines were operating at high torques and at speeds from 60 to 70 percent of the rated speed. The fuel consumption increased at an increasing rate as the torque was reduced; and, at 45 percent of maximum torque, the fuel consumption was 20 percent higher than at maximum torque when the engines were operating at 70 percent of rated speed. Minimum specific fuel consumption was obtained at the same air-fuel ratio regardless of compression ratio. No improvement in fuel consumption was obtained when mixtures leaner than an air-fuel ratio of 15.5 were used. The leanest mixture ratio on which the engine with the 1340-H cylinder would operate smoothly was 18.5 and the spark advance for maximum power with this mixture ratio was 50 degrees B.T.C. A method is discussed for reducing the amount of testing necessary to obtain curves for minimum brake fuel consumption.
    Type: NACA-TN-654
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  • 61
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    A flight investigation of the reduction of aileron operating force by means of fixed tabs and differential linkage, with notes on linkage design (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight tests were made to demonstrate the particularity of employing fixed tabs in conjunction with a suitably designed differential linkage to reduce the force required to operate ailerons. The tests showed the system to be practicable with tabs of the inset type. The relative ineffectiveness of attached tabs for changing the aileron floating angle rendered them unsuitable. Experience gained in the investigation has indicated that the use of the system is limited to maximum deflections of one aileron relative to the other of less than 30 degrees and that the differential linkage should always be designed on the basis of the highest probable floating angle.
    Type: NACA-TN-653
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  • 62
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    Hydrodynamic and Aerodynamic Tests of Four Models of Outboard Floats : (N.A.C.A. Models 51-A, 51-B, 51-C, and 51-D) (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Four models of outboard floats (N.A.C.A. models 51-A, 51-B, 51-C, and 51-D) were tested in the N.A.C.A. tank to determine their hydrodynamic characteristics and in the 20-foot wind tunnel to determine their aerodynamic drag. The results of the tests, together with comparisons of them, are presented in the form of charts. From the comparisons, the order of merit of the models is estimated for each factor considered. The best compromise between the various factors seems to be given by model 51-D. This model is the only one in the series with a transverse step.
    Type: NACA-TN-678
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  • 63
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    Tables of stiffness and carry-over factor for structural members under axial load (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tables of stiffness and carry-over factor are presented for members in which the cross section and axial load do not vary along the length of the member. These tables are of use in solving problems in the stability of structural members under axial load as well as in application of the Cross method of moment distribution when the effects of axial load in the members are considered. The interval between successive values of the argument is small enough to make interpolation unnecessary in engineering calculations.
    Type: NACA-TN-652
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  • 64
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    Effect of spark-timing regularity on the knock of engine performance (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests on a high-speed single-cylinder engine are described. The regularity of the spark timing was varied by driving the timer from different engine shafts. A simple and reasonably accurate method of determining the spark timing is described. The results show that irregular spark timing may cause large errors in tests of the knocking properties of fuels. For the engine tested, it was found that a change of one crankshaft degree in spark restart was equivalent to an 0.85 inch Hg change in allowable inlet pressure.
    Type: NACA-TN-651
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  • 65
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    The effect of air-passage length on the optimum fin spacing for maximum cooling (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect on cooling of baffle length with optimum cylinder finning is discussed. Results from tests of several streamlined cylinders are given. It is shown that by employing several baffles the cooling can be increased several times.
    Type: NACA-TN-649
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  • 66
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    Wind-tunnel tests of a Clark Y wing having split flaps with gaps (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made of the Clark Y wing having split flaps with a gap between the flap and the lower surface of the wing. Lift, drag, and pitching moments were measured for the wing with three different sizes of flap. It was found that any gap between the flap and the wing reduced the lift, the drag, and the pitching moments, but that the center-of-pressure movement and the ratio of lift to drag were little affected.
    Type: NACA-TN-650
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  • 67
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    The Increase in Frictional Resistance Caused by Various Types of Rivet Heads as Determined by Tests of Planing Surfaces (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The increase in the frictional resistance of a surface caused by the presence of rivet heads was determined by towing four planing surfaces of the same dimensions. One surface was smooth and represented a surface without rivet heads or one with perfectly flush countersunk rivets. The other three surfaces were each fitted with the same number of full-size rivet heads but of a different type arranged in the same pattern on each surface. The surfaces were towed at speeds representative of the high water speeds encountered by seaplanes during take-off and the range of Reynolds Number covered by the test was from 4 x 10(exp 6) to 18 x 10(exp 6). The rivet heads investigated were oval countersunk, brazier, and round for rivets having shanks 5/32 inch in diameter. The oval countersunk heads were sunk below the surface by dimpling the plating around them. The results of the tests showed that, for the rivet heads investigated, the increase in the friction coefficient of the surface is directly proportional to the height of the rivet head. The order of merit in regard to low resistance is flush countersunk, oval countersunk (whether sunk below the surface or not), brazier, and round.
    Type: NACA-TN-648
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  • 68
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    Engine Performance and Knock Rating of Fuels for High-output Aircraft Engines (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data are presented to show the effects of inlet-air pressure, inlet-air temperature, and compression ratio on the maximum permissible performance obtained on a single-cylinder test engine with aircraft-engine fuels varying from a fuel of 87 octane number to one 100 octane number plus 1 ml of tetraethyl lead per gallon. The data were obtained on a 5-inch by 5.75-inch liquid-cooled engine operating at 2,500 r.p.m. The compression ratio was varied from 6.50 to 8.75. The inlet-air temperature was varied from 120 to 280 F. and the inlet-air pressure from 30 inches of mercury absolute to the highest permissible. The limiting factors for the increase in compression ratio and in inlet-air pressure was the occurrence of either audible or incipient knock. The data are correlated to show that, for any one fuel,there is a definite relationship between the limiting conditions of inlet-air temperature and density at any compression ratio. This relationship is dependent on the combustion-gas temperature and density relationship that causes knock. The report presents a suggested method of rating aircraft-engine fuels based on this relationship. It is concluded that aircraft-engine fuels cannot be satisfactorily rated by any single factor, such as octane number, highest useful compression ratio, or allowable boost pressure. The fuels should be rated by a curve that expresses the limitations of the fuel over a variety of engine conditions.
    Type: NACA-TN-647
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  • 69
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    Wind-tunnel Tests of a 2-engine Airplane Model as a Preliminary Study of Flight Conditions Arising on the Failure of the Engine (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests of a 15-foot-span model of a two-engine low wing transport airplane were made as a preliminary study of the emergency arising from the failure of one engine in flight. Two methods of reducing the initial yawing moment resulting from the failure of one engine were investigated and the equilibrium conditions were explored for two basic modes on one engine, one with zero angle of sideslip and the other with several degrees of sideslip. The added drag resulting from the unsymmetrical attitudes required for flight on one engine was determined for the model airplane. The effects of the application of power upon the stability, controllability, lift, and drag of the model airplane were measured. A dynamic pressure survey of the propeller slipstream was made in the neighborhood of the tail surfaces at three angles of attack. The added parasite drag of the model airplane resulting from the unfavorable conditions of flight on one engine was estimated. From 35 to 50 percent of this added drag was due to the drag of the dead engine propeller and the other 50 to 65 percent was due to the unsymmetrical attitude of the airplane. The mode of flight on one engine in which the angle of sideslip was zero was found to require less power than the mode in which the angle of sideslip was several degrees.
    Type: NACA-TN-646
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  • 70
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    Some aspects of the stalling of modern low-lying monoplanes (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The factors affecting the stalling characteristics of modern airplanes are briefly discussed. The effect of present-day design trends is shown and means for improving the stalling characteristics of future airplanes are indicated.
    Type: NACA-TN-645
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  • 71
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    Flight and Wind-tunnel Tests of an XBM-1 Dive Bomber (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are given of pressure-distribution measurements made in flight over the right wing cellule and the right half of the horizontal tail surfaces of a dive-bombing biplane. Simultaneous measurements were also taken of the air speed, control-surface positions, control forces, and normal accelerations during various abrupt maneuvers in vertical plane. These maneuvers consisted of push-downs and pull-ups from level flight, dives and dive pull-ups from inverted flight. Besides the pressure measurements, flight tests were made to obtain (1) wing-fabric deflections during dives and (2) variation of the minimum drag coefficient with Reynolds Number. Supplementary tests were also done in the full-scale wind tunnel to obtain the characteristics of the airplane under various propeller conditions and with various tail settings. The results indicate that: (1) by increasing the fabric deflection between pressure ribs, the span load distribution was considerably modified near the center and the wing moment relations were changed; and (2) the minimum drag was less for the idling propeller than for the propeller locked in a vertical position. The value of C(sub D sub min) was equal to K(Reynolds Number)(exp -0.03) for a range from 2,800,000 to 13,100,000.
    Type: NACA-TN-644
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  • 72
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    A study of flying-boat take-off (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It is shown that the normal resistance curve for a flying boat may be approximated by two straight lines. The equations for take-off distance and time, derived from this approximation, are applied to a series of flying boats and the resulting factors are plotted in non dimensional form in a series of charts. Take-off performances from the charts are shown to be in good agreement with step-by-step integrations. Some applications of the charts to the solution of general design problems are included.
    Type: NACA-TN-643
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  • 73
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    Interference of Wing and Fuselage from Tests of 17 Combinations in the NACA Variable-density Tunnel Combination with Special Junctures (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of the wing-fuselage interference program in progress in the NACA variable-density wind tunnel, a method of eliminating the interference bubble associated with critical mid wing combinations was investigated. The interference bubble of the critical mid wing combination was shown to respond to modification at the nose of the juncture and to be entirely suppressed with little or no adverse effect on the high-speed drag by special leading edge fillets.
    Type: NACA-TN-641
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  • 74
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    Interference of Wing and Fuselage from Tests of Eight Combinations in the NACA Variable-density Tunnelcombinations with Tapered Fillets and Straight-side Junctures (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The round fuselage of an unfilleted low-wing combination was modified to incorporate straight-side junctures. The resulting combination, with or without horizontal tail surfaces, had practically the same aerodynamic characteristics as the corresponding round-fuselage tapered-fillet combination.
    Type: NACA-TN-642
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  • 75
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    Planing-surface Tests at Large Froude Numbers - Airfoil Comparison (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The take-off capacity of a flying boat depends upon the design of the hull bottom ahead as well as aft of the step. Systematic tests - largely made by industry itself - had proved the benefit accruing from a well designed hull bottom long before theoretical insight into the flow phenomena involved had been obtained. The theoretical framing of the problem was beset with serious difficulties and, though restricted to the processes within range of the planing bottom ahead of the step, the solutions do not yet afford a comprehensive survey.
    Type: NACA-TM-848
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  • 76
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    Twisting failure of centrally loaded open-section columns in the elastic range (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the following report a complete theory of twisting failure by the energy method is developed, based on substantially the same assumptions as those employed by Wagner and Bleich. Problems treated in detail are: the stress and strain condition under St. Venant twist and in twist with axial constraint; the concept of shear center and the energy method for problems of elastic stability.
    Type: NACA-TM-851
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  • 77
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    Experimental Study of Ignition by Hot Spot in Internal Combustion Engines (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to carry out the contemplated study, it was first necessary to provide hot spots in the combustion chamber, which could be measured and whose temperature could be changed. It seemed difficult to realize both conditions working solely on the temperature of the cooling water in a way so as to produce hot spots on the cylinder wall capable of provoking autoignition. Moreover, in the majority of practical cases, autoignition is produced by the spark plug, one of the least cooled parts in the engine. The first procedure therefore did not resemble that which most generally occurs in actual engine operation. All of these considerations caused us to reproduce similar hot spots at the spark plugs. The hot spots produced were of two kinds and designated with the name of thermo-electric spark plug and of metallic hot spot.
    Type: NACA-TM-873
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  • 78
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    Investigations on the downwash behind a tapered wing with fuselage and propeller (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The new downwash measurements behind a tapered wing with parallel center section described in the present report can be brought into good agreement with theoretical calculations if made on the basis of not-rolled-up vortex sheet and allowance is made for the lowering of the sheet. The test values are about 1 degree higher than the "upper limit" established for it, as against approximately 0.5 degrees in the earlier tests behind a rectangular and elliptical wing. The measurements on lateral axes, especially if lying below the wing on a level with the vortex train, disclosed in accord with the lift distribution, a marked change in angle over the span of the tail in contrast to the rectangular and elliptical wing.
    Type: NACA-TM-876
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  • 79
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    Flow in Smooth Straight Pipes at Velocities Above and Below Sound Velocity (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: To investigate the laws of flow of compressible fluids in pipes, tests were carried out with air flowing at velocities below and above that of sound in straight smooth pipes. Air was chosen as the flow medium. In order that the effect of compressibility may be brought out most effectively, the velocity should lie between 100 and 500 m/s (200 and 1,000 mph); that is, be of the order of magnitude of the velocity of sound in air. The behavior of the compression shock in a smooth cylindrical pipe was also investigated. The compression shock can occur at any position in the pipe, depending on the throttling downstream, and travels upstream with increasing throttling up to the pipe entrance, so that only subsonic velocities occur in the pipe.
    Type: NACA-TM-844
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  • 80
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    The Buckling of Curved Tension-field Girders (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present paper reports on experiments made to determine the buckling load under shear of circular curved tension-field webs. The buckling load of the webs may be expressed with reference to the buckling load of the stiffeners. It is found that within the explored range the buckling load is approximately twice as great as that of the identically stiffened flat wall of equal web depth.
    Type: NACA-TM-846
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  • 81
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    Comparison of free-spinning wind-tunnel results with corresponding full-scale spin results (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-737
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  • 82
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    Heat Transfer to Fuel Sprays Injected into Heated Gases (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a study made of the influence of several variables on the pressure decrease accompanying injection of a relatively cool liquid into a heated compressed gas. Indirectly, this pressure decrease and the time rate of change of it are indicative of the total heat transferred as well as the rate of heat transfer between the gas and the injected liquid. Air, nitrogen, and carbon dioxide were used as ambient gases; diesel fuel and benzene were the injected liquids. The gas densities and gas-fuel ratios covered approximately the range used in compression-ignition engines. The gas temperatures ranged from 150 degrees c. to 350 degrees c.
    Type: NACA-TR-580
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  • 83
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    Tests of Five Full-Scale Propellers in the Presence of a Radial and a Liquid-Cooled Engine Nacelle, Including Tests of Two Spinners (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests are reported of five 3-blade 10-foot propellers operating in front of a radial and a liquid-cooled engine nacelle. The range of blade angles investigated extended from 15 degrees to 45 degrees. Two spinners were tested in conjunction with the liquid-cooled engine nacelle. Comparisons are made between propellers having different blade-shank shapes, blades of different thickness, and different airfoil sections. The results show that propellers operating in front of the liquid-cooled engine nacelle had higher take-off efficiencies than when operating in front of the radial engine nacelle; the peak efficiency was higher only when spinners were employed. One spinner increased the propulsive efficiency of the liquid-cooled unit 6 percent for the highest blade-angle setting investigated and less for lower blade angles. The propeller having airfoil sections extending into the hub was superior to one having round blade shanks. The thick propeller having a Clark y section had a higher take-off efficiency than the thinner one, but its maximum efficiency was possibly lower. Of the three blade sections tested, Clark y, R.A.F. 6, and NACA 2400-34, the Clark y was superior for the high-speed condition, but the R.A.F. 6 excelled for the take-off condition.
    Type: NACA-TR-642
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  • 84
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    The Torsional and Bending Deflection of Full-Scale Aluminum-Alloy Propeller Blades Under Normal Operating Conditions (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The torsional deflection of the blades of three full-scale aluminum-alloy propellers operating under various loading conditions was measured by a light-beam method. Angular bending deflections were also obtained as an incidental part of the study. The deflection measurements showed that the usual present-day type of propeller blades twisted but a negligible amount under ordinary flight conditions. A maximum deflection of about 1/10 degree was found at a v/nd of 0.3 and a smaller deflection at higher values of v/nd for the station at 0.70 radius. These deflections are much smaller than would be expected from earlier tests, but the light-beam method is considered to be much more accurate than the direct-reading-transit method used in the previous test.
    Type: NACA-TR-644
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  • 85
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    The Negative Thrust and Torque of Several Full-scale Propellers and Their Application to Various Flight Problems (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Negative thrust and torque data for 2, 3, and 4-blade metal propellers having Clark y and R.A.F. 6 airfoil sections were obtained from tests in the NACA 20-foot tunnel. The propellers were mounted in front of a radial engine nacelle and the blade-angle settings covered in the tests ranged from l5 degrees to 90 degrees. One propeller was also tested at blade-angle settings of 0 degree, 5 degrees, and 10 degrees. A considerable portion of the report deals with the various applications of the negative thrust and torque to flight problems. A controllable propeller is shown to have a number of interesting, and perhaps valuable, uses within the negative thrust and torque range of operation. A small amount of engine-friction data is included to facilitate the application of the propeller data.
    Type: NACA-TR-641
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  • 86
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    The Aerodynamic Characteristics of Full-Scale Propellers Having 2, 3, and 4 Blades of Clark Y and R.A.F. 6 Airfoil Sections (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic tests were made of seven full-scale 10-foot-diameter propellers of recent design comprising three groups. The first group was composed of three propellers having Clark y airfoil sections and the second group was composed of three propellers having R.A.F. 6 airfoil sections, the propellers of each group having 2, 3, and 4 blades. The third group was composed of two propellers, the 2-blade propeller taken from the second group and another propeller having the same airfoil section and number of blades but with the width and thickness 50 percent greater. The tests of these propellers reveal the effect of changes in solidity resulting either from increasing the number of blades or from increasing the blade width propeller design charts and methods of computing propeller thrust are included.
    Type: NACA-TR-640
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  • 87
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    Approximate Stress Analysis of Multistringer Beams with Shear Deformation of the Flanges (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The problem of the skin-stringer combinations used as axially loaded panels or as covers for box beams is considered from the point of view of the practical stress analyst. By a simple substitution the problem is reduced to the problem of the single-stringer structure, which has been treated in NACA Report no. 608. The method of making this substitution is essentially empirical; in order to justify it, comparisons are shown between calculations and strain-gage tests of three beams tested by the author and of one compression panel and three beams tested and reported elsewhere.
    Type: NACA-TR-636
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  • 88
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    The experimental and calculated characteristics of 22 tapered wings (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The experimental and calculated aerodynamic characteristics of 22 tapered wings are compared, using tests made in the variable-density wind tunnel. The wings had aspect ratios from 6 to 12 and taper ratios from 1:6:1 and 5:1. The compared characteristics are the pitching moment, the aerodynamic-center position, the lift-curve slope, the maximum lift coefficient, and the curves of drag. The method of obtaining the calculated values is based on the use of wing theory and experimentally determined airfoil section data. In general, the experimental and calculated characteristics are in sufficiently good agreement that the method may be applied to many problems of airplane design.
    Type: NACA-TR-627
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  • 89
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    Column strength of tubes elastically restrained against rotation at the ends (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a study made of the effects of known end restraint on commercially available round and streamline tubing of chromium-molybdenum steel, duralumin, stainless steel, and heat-treated chromium-molybdenum steel; and a more accurate method than any previously available, but still a practical method, was developed for designing compression members in riveted or welded structures, particularly aircraft. Two hundred specimens were tested as short, medium-length, and long columns with freely supported ends or elastically restrained ends. Tensile and compressive tests were made on each piece of original tubing from which column specimens were cut.
    Type: NACA-TR-615
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  • 90
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    Two-dimensional subsonic compressible flow past elliptic cylinders (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The method of Poggi is used to calculate, for perfect fluids, the effect of compressibility upon the flow on the surface of an elliptic cylinder at zero angle of attack and with no circulation. The result is expressed in a closed form and represents a rigorous determination of the velocity of the fluid at the surface of the obstacle insofar as the second approximation is concerned. Comparison is made with Hooker's treatment of the same problem according to the method of Janzen and Rayleight and it is found that, for thick elliptic cylinders, the two methods agree very well. The labor of computation is considerably reduced by the present solution.
    Type: NACA-TR-624
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  • 91
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    Pressure distribution over an NACA 23012 airfoil with a slotted and a plain flap (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of pressure-distribution of an NACA 23012 airfoil equipped with a slotted flap and with a plain flap conducted in the 7 by 10-foot wind tunnel. A test installation was used in which the 7-foot-span airfoil was mounted vertically between the upper and lower sides of the closed test section so that two-dimensional flow was approximated. The pressures were measured on the upper and lower surfaces at one chord section both on the main airfoil and on the flaps for several different flap deflections and at several angles of attack. The data are presented in the form of pressure-distribution diagrams and as graphs of calculated section coefficients for the airfoil-and-flap combinations and also for the flaps alone. The results are useful for application to rib and flap structural design; in addition, the plain-flap data furnish considerable information applicable to the structural design of plain ailerons.
    Type: NACA-TR-633
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  • 92
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    A Photographic Study of Combustion and Knock in a Spark-Ignition Engine (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a photographic study of the combustion in a spark-ignition engine using both Schlieren and flame photographs taken at high rates of speed. Although shock waves are present after knock occurs, there was no evidence of any type of sonic or supersonic compression waves existing in the combustion gases prior to the occurrence of knock. Artificially induced shock waves in the engine did not in themselves cause knock. The photographs also indicate that, although auto-ignition ahead of the flame front may occur in conjunction with knock, it is not necessary for the occurrence of knock. There is also evidence that the reaction is not completed in the flame front but continues for some time after the flame front has passed through the charge.
    Type: NACA-TR-622
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  • 93
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    Drag of cylinders of simple shapes (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to determine the effect of shape, compressibility, and Reynolds number on the drag and critical speed for simple forms, the drag forces on models of various simple geometric cross sections were measured in the NACA 11-inch high-speed wind tunnel. The models were circular, semitubular, elliptical, square, and triangular (isosceles) cylinders. They were tested over a speed range from 5 percent of the speed of sound to a value in excess of the critical speed, corresponding, for each model, approximately to a tenfold Reynolds number range, which extended from a minimum of 840 for the smallest model to a maximum of 310,000 for the largest model.
    Type: NACA-TR-619
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  • 94
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    Heat-stressed structural components in combustion-engine design (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Heated structural parts alter their shape. Anything which hinders free heat expansion will give rise to heat stresses. Design rules are thus obtained for the heated walls themselves as well as for the adjoining parts. An important guiding principle is that of designing the heat-conducting walls as thin as possible.
    Type: NACA-TM-875
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  • 95
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    Systematic Airfoil Tests in the Large Wind Tunnel of the DVL (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present report is a description of systematic tests at maximum lift on airfoils with and without split flap and of profile drag at low lift. In order to obtain an opinion as to the suitability of the airfoils with flaps, the maximum-lift measurements were repeated on airfoils with split flaps. The profile drag at low lift was arrived at by direct weighing and momentum measurements and, since the profiles were of unusual depth, extended to large Reynolds numbers.
    Type: NACA-TM-852
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  • 96
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    Model Experiments on the Forces and Moments Acting on an End Plate Fitted to a Wing (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper reports on 4-component balance measurements with and without angle of sideslip made on an airfoil with end plate at one tip. In addition, pressure distribution measurements on the end plate served as a basis for the determination of the forces on the end plate and for the bending moments.
    Type: NACA-TM-855
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  • 97
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    The Design of Floats (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Following a summary of the multiplicity of domestic and foreign floats and a brief enumeration of the requirements of floats, the essential form parameters and their effect on the qualities of floats are detailed. On this basis a standard float design is developed which in model families with varying length/beam ratio and angle of dead rise is analyzed by an experimental method which permits its best utilization on any airplane.
    Type: NACA-TM-860
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  • 98
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    Compression struts with nonprogressively variable moment of inertia (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The buckling failure conditions for a bar with nonprogressively variable moment of inertia J(sub n), although constant over length l(sub n), are developed.
    Type: NACA-TM-861
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  • 99
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    The Influence of Notches Under Static Stress (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: From the described experiments it is seen that notches are a potential source of strength decrease even under static stress, which the designer must take into consideration. Section I is a general treatment of notch influence under the various types of stresses. Section II treats the influence of notches in thin sheet as is used in airplane construction.
    Type: NACA-TM-862
    Format: application/pdf
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  • 100
    facet.materialart.
    Unknown
    Theoretical Study of Various Airplane Motions After Initial Disturbance (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present investigation may be considered as preliminary to the study of automatic stabilizers. We have sought to determine first how an airplane of average characteristics reacts against the principal disturbances it may encounter. Without entering into the general study of automatic stabilizers, the present work suggests the idea of a stabilizer whose sensitive member would be a wind vane or pressure plate. The elements considered as variable were the coefficients of static stability - that is, the derivatives of the coefficients of the moments with respect to the angles of attack and of yaw; these angles may be determined by the vanes.
    Type: NACA-TM-867
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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