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  • 1
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    Is present tilting in North America due to glacial melting (1932)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 58, no. 3, pp. 67-68, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Tectonics ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Experiments testing seismographic methods for determining crustal structure (1932)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 58, no. 3, pp. 65-66, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Travel time curves at small distances and wave velocities in Southern California (1932)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 35, no. 3, pp. 6-45, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Travel time ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Berichtigungen und Ergänzungen zu Band 4 (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 4: Erdbeben (finished), 12+ 1202 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1186-1190, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Seismology ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Der Aufbau der Atmosphäre (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 9: Physik der Atmosphäre 2 (only 1., 2., and 3. part), 8 + 698 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1-88, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Meteorology
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Mit welcher Genauigkeit läßt sich die Schallgeschwindigkeit in der Stratosphäre finden? (1932)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 35, no. 3, pp. 46-50, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Velocity analysis ; Meteorology ; Acoustics
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Structure of the earth's crust derived from seismograms (1932)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 43, no. 3, pp. 236-237, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: CRUST ; Seismology ; Seismics (controlled source seismology)
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    The earthquake in Santa Monica Bay, California, on August 30, 1930 (1932)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 22, no. 3, pp. 138-154, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismology ; Earthquake ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Experiments testing seismographic methods for determining crustal structure (1932)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 22, no. 3, pp. 185-246, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Die Schallausbreitung in der Atmosphäre (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 9: Physik der Atmosphäre 2 (only 1., 2., and 3. part), 8 + 698 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 89-145, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Meteorology ; Wave propagation ; Acoustics
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    The command system malfunction of the telstar satellite (1932)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Command system malfunction of telstar satellite due to transistor surface damage in redundant command decoder
    Keywords: COMPUTERS
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    NASA TECHNICAL REPORTS
  • 12
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    Test of NACA 21 Airfoil (Modified NACA M-6) Including Characteristics at Positive and Negative Angles of Attack (1932)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance; Research and Support Facilities (Air); Aerodynamics
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    NASA TECHNICAL REPORTS
  • 13
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    The German Investigation of the Accident at Meopham (England) (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is a recounting of the German investigation of the crash of a commercial Junkers F 13 ge in England. The English report is examined and compared with the German interpretation of the accident.
    Type: NACA-TM-669
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  • 14
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    Development of tailless and all-wing gliders and airplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tailless airplanes are characterized by having all their control surfaces, especially the elevator, incorporated in the wings. This paper provides a discussion of the history of their development and current state of development.
    Type: NACA-TM-666
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  • 15
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    Twelfth Rhon soaring contest, 1931 (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The crew of the "Fafnir" was given an excellent opportunity for collecting first-hand data as to the usefulness of gliders in the Alps. It is necessary to recount the remarkable glider achievements ahead of the Rhon Soaring Contest, in order to understand the tension and expectation with which the Rhon contest was anticipated.
    Type: NACA-TM-671
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  • 16
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    Towing tests of models as an aid in the design of seaplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report concerns the making and evaluation of a towing test of a seaplane float system. Some of the topics considered are: 1) the influence of the wing cell and power plant on the take-off performance; 2) the determination of the resistance curve for the take-off free to trim; 3) the resistance curves with elevator control (at fixed trims); 4) take-off time and take-off run.
    Type: NACA-TM-676 , Gesellschaft der Freunde und Forderer der Hamburgischen Schiffbau-Versuchsanstalt (9th : June 11, 1930)
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  • 17
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    Airplane stability in taxying (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stability analysis of an airplane while rolling is much more simplified to the extent that it can be obtained for numerical data which can be put to practical use in the design of landing gear dimensions. Every landing gear type attains to a critical ground friction coefficient that decides the beginning of instability, i.e., nosing over. This study has, in addition, a certain interest for the use of wheel brakes.
    Type: NACA-TM-682
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  • 18
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    Speed and pressure recording in three-dimensional flow (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Van der Megge Zijnen's spherical Pitot tube with its 5 test holes insures a simultaneous record of static pressure and magnitude and direction of velocity in three-dimensional flow. The report treats the method as well as the range of application of this Pitot in the light of modern knowledge on flow around spheres.
    Type: NACA-TM-688
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  • 19
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    The Problem of Tire Sizes for Airplane Wheels (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: On the basis of experiments and theoretical considerations a proposal is made for a standard tire series for airplane wheels, without regard to existing standards.
    Type: NACA-TM-689
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    NASA TECHNICAL REPORTS
  • 20
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    Combustion Velocity of Benzine-Benzol-Air Mixtures in High-Speed Internal-Combustion Engines (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present paper describes a device whereby rapid flame movement within an internal-combustion engine cylinder may be recorded and determined. By the aid of a simple cylindrical contact and an oscillograph the rate of combustion within the cylinder of an airplane engine during its normal operation may be measured for gas intake velocities of from 30 to 35 m/s and for velocities within the cylinder of from 20 to 25 m/s. With it the influence of mixture ratios, of turbulence, of compression ratio and kind of fuel on combustion velocity may be determined. Besides the determination of the influence of the above factors on combustion velocity, the degree of turbulence may also be determined. As a unit of reference in estimating the degree of turbulence, the intake velocity of the charge is chosen.
    Type: NACA-TM-668
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  • 21
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    Vertical descent of the autogiro (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this report is to show that only part of the system of rotating blades really is in the "windmill decelerating attitude" when the profile drag is sufficiently low. This particular part receives more torque from the air loads than can be absorbed by the profile drag. As a result thereof the rotating autogiro blade, when its torque is zero, is in part a propeller which functions in the "annular vortex attitude."
    Type: NACA-TM-673
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  • 22
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    Stresses developed in seaplanes while taking off and landing (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the case of seaplanes, the lack of elastic shock absorbers, the presence of which might be quite dangerous, especially in taking off, makes it necessary to give some consideration to the phenomenon of landing. Special consideration must be given the process of taking off, since even moderately rough water may develop rather large stresses. The purpose of this communication is to show what has been accomplished in Italy and other countries and to draw a few useful conclusions.
    Type: NACA-TM-677 , Societa Italiana per il Progresso delle Scienze (20th : 1931 : Milan, Italy)
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  • 23
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    The Aerodynamic Characteristics of a Slotted Clark Y Wing as Affected by the Auxiliary Airfoil Position (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests on a slotted Clark Y wing were conducted in a vertical wind tunnel to determine the best position for a given auxiliary airfoil with respect to the main wing. A systematic series of 100 changes in location of the auxiliary airfoil were made to cover all the probable useful ranges of slot gap, slot width, and slot depth. The results of the investigation may be applied to the design of automatic or controlled slots on wings with geometric characteristics similar to the wing tested. The best positions of the auxiliary airfoil were covered by the range of the tests, and the position for desired aerodynamic characteristics may easily be obtained from charts prepared especially for the purpose.
    Type: NACA-TR-400
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  • 24
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    Flame Movement and Pressure Development in an Engine Cylinder (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation describes a visual method for making stroboscopic observations, through a large number of small windows, of the spread of flame throughout the combustion chamber of a gasoline engine. Data, secured by this method on a small engine burning gaseous fuels, are given to show the effects of mixture ratio, spark advance, engine speed, charge density, degree of dilution, compression ratio, and fuel composition on flame movement in the cylinder. Partial indicator diagrams showing pressure development during the combustion period are included. Although present knowledge is not sufficient to permit qualitative evaluation of the separate effects on flame movement of chemical reaction velocity, thermal expansion of burned gases, resonance, turbulence, and piston movement, the qualitative influence of certain of these factors on some of the diagrams is indicated.
    Type: NACA-TR-399
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    NASA TECHNICAL REPORTS
  • 25
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    Investigation of Damping Liquids for Aircraft Instruments : II (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data are presented on the kinematic viscosity, in the temperature range -50 degrees to +30 degrees C. of pure liquids and of solutions of animal oils, vegetable oils, mineral oils, glycerine, and ethylene glycol in various low freezing point solvents. It is shown that the thermal coefficient of kinematic viscosity as a function of the kinematic viscosity of the solutions of glycerine and ethylene glycol in alcohols is practically independent of the temperature and the chemical composition of the individual liquids. This is similarly true for the mineral oil group and, for a limited temperature interval, for the pure animal and vegetable oils. The efficiency of naphthol, hydroquinone, and diphenylamine to inhibit the change of viscosity of poppyseed and linseed oils was also investigated.
    Type: NACA-TR-398
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  • 26
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    Full-Scale Tests of Metal Propellers at High Tip Speeds (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes tests of 10 full-scale metal propellers of several thickness ratios at various tip speeds up to 1,350 feet per second. The results indicate no loss of efficiency up to tip speeds of approximately 1,000 feet per second. Above this tip speed the loss is at a rate of about 10 per cent per 100 feet per second increase relative to the efficiency at the lower speeds for propellers of pitch diameter ratios 0.3 to 0.4. Propellers having sections of small thickness ratio can be run at slightly higher speeds than thick ones before beginning to lose efficiency.
    Type: NACA-TR-375
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  • 27
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    Present status of aircraft instruments (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a brief description of the present state of development and of the performance characteristics of instruments included in the following group: speed instruments, altitude instruments, navigation instruments, power-plant instruments, oxygen instruments, instruments for aerial photography, fog-flying instruments, general problems, summary of instrument and research problems. The items considered under performance include sensitivity, scale errors, effects of temperature and pressure, effects of acceleration and vibration, time lag, damping, leaks, elastic defects, and friction.
    Type: NACA-TR-371
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  • 28
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    A new chart for estimating the absolute ceiling of an airplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is concerned with the derivation of a chart for estimating the absolute ceiling of an airplane. This chart may be used in conjunction with the usual curves of power required and power available as an accurate substitute for extended calculation, or it may be used in the estimation of absolute ceiling when power curves are not available.
    Type: NACA-TR-368
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  • 29
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    Maneuverability Investigation of the F6C-3 Airplane with Special Flight Instruments (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made for the purpose of obtaining information on the maneuverability of the F6C-3 airplane. It is the first of a series of similar investigations to be conducted on a number of military airplanes for the purpose of comparing the abilities of these airplanes to maneuver, and also to establish a fund of quantitative data which may be used in formulating standards of comparison for rating the maneuverability of any airplane. A large part of this initial investigation was necessarily devoted to the development and trial of methods suitable for use in subsequent investigations of this nature. Air speed, angular velocity, linear acceleration, and position of the control surfaces were measured by instruments in the airplane during loops, push-downs, pull-outs from dives, pull-ups from level flight, barrel rolls, and spins. The coordinates of flight paths were deduced from the data whenever possible, and were checked in some cases by the use of a camera obscura. The results are given in curves showing the variation of the measured quantities with respect to time, and maximum values are tabulated.
    Type: NACA-TR-369
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  • 30
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    Annual report of the National Advisory Committee for Aeronautics (17th).administrative report including Technical Report nos. 365 to 400 (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
    Type: NACA-AR-17
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  • 31
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    The drag characteristics of several airships determined by deceleration tests (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of deceleration tests conducted for the purpose of determining the drag characteristics of six airships. The tests were made with airships of various shapes and sizes belonging to the Army, the Navy, and the Goodyear-Zeppelin Corporation. Drag coefficients for the following airships are shown: Army TC-6, TC-10, and TE-2; Navy Los Angeles and ZMC-2; Goodyear Puritan. The coefficients vary from about 0.045 for the small blunt airships to 0.023 for the relatively large slender Los Angeles. This variation may be due to a combination of effects, but the most important of these is probably the effect of length-diameter ratio.
    Type: NACA-TR-397
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  • 32
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    The Effect of Valve Timing Upon the Performance of a Supercharged Engine at Altitude and an Unsupercharged Engine at Sea Level (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted to determine the comparative effects of valve timing on the performance of an unsupercharged engine at sea level and a supercharged engine at altitude. The tests were conducted on the NACA universal test engine. The timing of the four valve events was varied over a wide range; the engine speeds were varied between 1,050 and 1,500 r.p.m.; the compression ratios were varied between 4.35:1 and 7.35:1. The conditions of exhaust pressure and carburetor pressure of a supercharged engine were simulated for altitudes between 0 and 18,000 feet. The results show that optimum valve timing for a supercharged engine at an altitude of 18,000 feet differs slightly from that for an unsupercharged engine at sea level. A small increase in power is obtained by using the optimum timing for 18,000 feet for altitudes above 5,000 feet. The timing of the intake opening and exhaust closing becomes more critical as the compression ratio is increased.
    Type: NACA-TR-390
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  • 33
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    The Effect of Small Angles of Yaw and Pitch on the Characteristics of Airplane Propellers (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of wind tunnel tests to determine the effect on the characteristics of a propeller of inclining the propeller axis at small angles to the relative wind. Tests were made of a full-scale propeller and fuselage combination at four angles of yaw (0 degree, +5 degrees, +10 degrees, +15 degrees), and of a model propeller, nacelle, and wing combination of five angles of pitch (-5 degrees, 0 degree, +5 degrees, +10 degrees and +15 degrees). The results of the full-scale tests of a propeller and fuselage, without a wing, show that the effect on the propeller performance is small. Similar results are shown by the model test data except that where the propeller is directly in front of the wing there is an appreciable decrease in effective thrust and propulsive efficiency with increase of angle of pitch.
    Type: NACA-TR-389
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  • 34
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    The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of wind tunnel tests on a group of eight very thick airfoils having sections of the same thickness as those used near the roots of tapered airfoils. The tests were made to study certain discontinuities in the characteristic curves that have been obtained from previous tests of these airfoils, and to compare the characteristics of the different sections at values of the Reynolds number comparable with those attained in flight. The discontinuities were found to disappear as the Reynolds number was increased. The results obtained from the large-scale airfoil, a symmetrical airfoil having a thickness ratio of 21 per cent, has the best general characteristics.
    Type: NACA-TR-391
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  • 35
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    Comparison of Full-Scale Propellers Having R.A.F.-6 and Clark Y Airfoil Sections (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report the efficiencies of two series of propellers having two types of blade sections are compared. Six full-scale propellers were used, three having R. A. F.-6 and three Clark Y airfoil sections with thickness/chord ratios of 0.06, 0.08, and 0.10. The propellers were tested at five pitch setting, which covered the range ordinarily used in practice. The propellers having the Clark Y sections gave the highest peak efficiency at the low pitch settings. At the high pitch settings, the propellers with R. A. F.-6 sections gave about the same maximum efficiency as the Clark Y propellers and were more efficient for the conditions of climb and take-off.
    Type: NACA-TR-378
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  • 36
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    Rolling Moments Due to Rolling and Yaw for Four Wing Models in Rotation (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a series of autorotation and torque tests on four different rotating wing systems at various rates of roll and at several angles of yaw. The investigation covered an angle of attack range up to 90 degrees and angles of yaw of 0 degree, 5 degrees, 10 degrees, and 20 degrees. The tests were made in a 5-foot, closed-throat atmospheric wind tunnel. The object of the tests was primarily to determine the effects of various angles of yaw on the rolling moments of the rotating wings up to large angles of attack. It was found that at angles of attack above that of maximum lift the rolling moments on the wings due to yaw (or side slip) from 5 degrees to 20 degrees were roughly of the same magnitude as those due to rolling. There was a wide variation in magnitude of the rolling moment due to yaw angle. The rates and ranges of stable autorotation for the monoplane models were considerably increased by yaw, whereas for an unstaggered biplane they were little affected. The immediate cause of the rolling moment due to yaw is apparently the building up of large loads on the forward wing tip and the reduction of loads on the rearward wing tip.
    Type: NACA-TR-379
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  • 37
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    The Stieger ST. 4 light airplane (British) : a twin-engine four-seat low-wing cabin monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-164
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  • 38
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    The Farman night bombers 211 and 212 (French) : four-engine high-wing monoplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-165
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  • 39
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    Supplement to the Supermarine S.6.B. Racing Seaplane (British) : A Low-Wing Twin-Float Monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-154-Suppl
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  • 40
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    Strength Tests on Thin-walled Duralumin Cylinders in Torsion (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is the first of a series presenting the results of strength tests on thin-walled cylinders and truncated cones of circular and elliptical section; it comprises the results obtained to date from torsion (pure shear) tests on 65 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The effect of variations in the length/radius and radius/thickness ratios on the type of failure is indicated, and a semi-empirical equation for the shearing stress at maximum load is given.
    Type: NACA-TN-427
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  • 41
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    Comparative Performance of a Powerplus Vane-type Supercharger and an N.A.C.A. Roots-type Supercharger (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests of a Power plus supercharger and a comparison of its performance with the performance previously obtained with an N.A.C.A. Roots-type supercharger. The Powerplus supercharger is a positive displacement blower of the vane type having mechanically operated vanes, the movement of which is controlled by slots and eccentrics. The supercharger was tested at a range of pressure differences from 0 to 15 inches of mercury and at speeds from 500 to 2,500 r.p.m. The pressure difference across the supercharger was obtained by throttling the intake of a depression tank which was interposed in the air duct between the supercharger and the Durley orifice box used for measuring the air. The results of these tests show that at low pressure differences and at all speeds the power required by the Powerplus supercharger to compress a definite quantity of air per second is considerably higher than that required by the Roots. At pressure differences from 10 to 14 inches of mercury and at speeds over 2,000 r.p.m. the power requirements of the two superchargers are practically the same. At a pressure difference of 15 inches of mercury or greater and at a speed of 2,500 r.p.m. or greater the performance of the Powerplus supercharger is slightly better than that of the Roots. Because the Powerplus supercharger cannot be operated at a speed greater than 3,000 r.p.m. as compared with 7,000 r.p.m. for the Roots, its capacity is approximately one-half that of the Roots for the same bulk. The Powerplus supercharger is more complicated and less reliable than the Roots supercharger.
    Type: NACA-TN-426
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  • 42
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    Methods of Visually Determining the Air Flow Around Airplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes methods used by the National Advisory Committee for Aeronautics to study visually the air flow around airplanes. The use of streamers, oil and exhaust gas streaks, lampblack and kerosene, powdered materials, and kerosene smoke is briefly described. The generation and distribution of smoke from candles and from titanium tetrachloride are described in greater detail because they appear most advantageous for general application. Examples are included showing results of the various methods.
    Type: NACA-TN-425
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  • 43
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    Preliminary Photomicrographic Studies of Fuel Sprays (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Photomicrographs were taken of fuel sprays injected into air at various densities for the purpose of studying the spray structure and the stages in the atomization of the fuel. The photomicrographs were taken at magnifying powers of 2.5, 3.25, and 10, using a spark discharge of very short duration for illumination. The results indicate that the theory advanced by Dr. R. A. Castleman, Jr., on the atomization of fuel in carburetors may also be applied to the atomization of fuel sprays of the solid-injection type. The fuel leaves the nozzle as a solid column, is ruffled and then torn into small, irregular ligaments by the action of the air. These ligaments are then quickly broken up into drops by the surface tension of the fuel. The photomicrographs also show that the dispersion of a fuel spray at a given distance from the nozzle increases with an increase in the jet velocity or an increase in the air density. The first portions of fuel sprays injected from an automatic injection valve into air at atmospheric density have a much greater dispersion than the later portions, but this difference decreases rapidly as the air density is increased.
    Type: NACA-TN-424
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  • 44
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    Effect of length of Handley Page tip slots on the lateral-stability factor, damping in roll (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests have been made in the NACA 7 by 10 foot wind tunnel on a Clark Y wing model equipped with various lengths of Handley Page slots extending inward from the wing tips. The slot lengths tested ranged from 20 to 100 per cent of the semi span. The effect of slot lengths on damping in roll was determined by means of both free-autorotation and forced-rotation test. In addition, the maximum lift coefficient was found with each slot length. The optimum length of slot for satisfactory damping in roll over a large range of angles of attack was found to be slightly over 50 per cent of the semispan for the form of slot tested.
    Type: NACA-TN-423
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  • 45
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    The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear. The highest value of C(sub L max), which was obtained with the largest flap hinged at 90 per cent of the chord from the leading edge, was 2.52 as compared with 1.27 for the basic wing.
    Type: NACA-TN-422
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  • 46
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    The pressure distribution over a long elliptical wing tip on a biplane in flight (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results of flight pressure-distribution tests on the right upper wing panel of a Douglas M-3 airplane equipped with an elliptical tip of length equal to the wing chord. The results are given in such form that the load distribution for any normal-force coefficient within the usual range encountered in flight may easily be determined.
    Type: NACA-TN-437
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  • 47
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    The Nature of Air Flow About the Tail of an Airplane in a Spin (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Air flow about the fuselage and empennage during a high-angle-of-attack spin was made visible in flight by means of titanium-tetrachloride smoke and was photographed with a motion-picture camera. The angular relation of the direction of the smoke streamer to the airplane axes was computed and compared with the angular direction of the motion in space derived from instrument measurement of the spin of the airplane for a nearly identical mass distribution. The results showed that the fin and upper part of the rudder were almost completely surrounded by dead air, which would render them inoperative; that the flow around the lower portion of the rudder and the fuselage was nonturbulent; and that air flowing past the cockpit in a high-angle-of-attack spin could not subsequently flow around control surfaces.
    Type: NACA-TN-421
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  • 48
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    The Effect of Propellers and Nacelles on the Landing Speeds of Tractor Monoplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper reports wind-tunnel tests giving the lift coefficients of large-scale wing-nacelle combinations both with and without the propeller. The tests were made to show the effect of nacelles, and idling and stopped propellers on the landing speeds of tractor monoplanes. Four types of nacelles with various cowlings were used in numerous positions with respect to both a Clark Y and a thick airfoil. The effect of both the idling and stopped propeller on lift, and consequently on landing speed, was negligible. A nacelle with exposed engine cylinders when placed directly in front of an airfoil caused a slight reduction in lift, consequently an increase in landing speed, over the condition with the wing alone. With this exception no appreciable effect on landing speed was indicated for any of the other combinations.
    Type: NACA-TN-420
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  • 49
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    The Effect of Connecting-passage Diameter on the Performance of a Compression-ignition Engine with a Precombustion Chamber (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of motoring tests are presented showing the effect of passage diameter on chamber and cylinder compression pressures, maximum pressure differences, and f.m.e.p. over a speed range from 300 to 1,750 r.p.m. Results of engine performance tests are presented which show the effect of passage diameter on m.e.p., explosion pressures, specific fuel consumption, and rates of pressure rise for a range of engine speeds from 500 to 1,500 r.p.m. The cylinder compression pressure, the maximum pressure difference, and the f.m.e.p. decreased rapidly as the passage diameter increased to 29/64 inch, whereas further increase in passage diameter effected only a slight change. The most suitable passage diameter for good engine performance and operating characteristics was 29/64 inch. Passage diameter became less critical with a decrease in engine speed. Therefore, the design should be based on maximum operating speed. Optimum performance and satisfactory combustion control could not be obtained by means of any single diameter of the connecting passage.
    Type: NACA-TN-436
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  • 50
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    Wind-tunnel Tests of the Fowler Variable-area Wing (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The lift, drag, and center of pressure characteristics of a model of the Fowler variable-area wing were measured in the NACA 7 by 10 foot wind tunnel. The Fowler wing consists of a combination of a main wing and an extension surface, also of airfoil section. The extension surface can be entirely retracted within the lower rear portion of the main wing or it can be moved to the rear and downward. The tests were made with the nose of the extension airfoil in various positions near the trailing edge of the main wing and with the surface at various angular deflections. The highest lift coefficient obtained was C(sub L) = 3.17 as compared with 1.27 for the main wing alone.
    Type: NACA-TN-419
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  • 51
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    Compression-ignition engine tests of several fuels (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests reported in this paper were made to devise simple engine tests which would rate fuels as to their comparative value and their suitability for the operating conditions of the individual engine on which the tests are made. Three commercial fuels were used in two test engines having combustion chambers with and without effective air flow. Strictly comparative performance tests gave almost identical results for the three fuels. Analysis of indicator cards allowed a differentiation between fuels on a basis of rates of combustion. The same comparative ratings were obtained by determining the consistent operating range of injection advance angle for the three fuels. The difference in fuels is more pronounced in a quiescent combustion chamber than in one with high-velocity air flow. A fuel is considered suitable for the operating conditions of an engine with a quiescent combustion chamber if it permits the injection of the fuel to be advanced beyond the optimum without exceeding allowable knock or allowable maximum cylinder pressures.
    Type: NACA-TN-418
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  • 52
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    The pressure distribution over a standard and a modified Navy elliptical wing tip on a biplane in flight (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results of flight pressure distribution tests on the right upper wing panel of a Douglas M-3 airplane equipped in turn with a standard Navy elliptical tip and a tip having the same plan form but modified in its front elevation from the swept-up aspect of the standard tip to a symmetrical aspect. The results are given in such form that the load distribution for any normal-force coefficient within the usual range encountered in flight may easily be determined. The results indicate that the modification in front elevation of the tip had no appreciable effect on the load distribution.
    Type: NACA-TN-433
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  • 53
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    The Effect of Clearance Distribution on the Performance of a Compression-ignition Engine with a Precombustion Chamber (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The clearance distribution in a precombustion chamber cylinder head was varied so that for a constant compression ratio of 13.5 the spherical auxiliary chambers contained 20, 35, 50, and 70 per cent of the total clearance volume. Each chamber was connected to the cylinder by a single circular passage, flared at both ends, and of a cross-sectional area proportional to the chamber volume, thereby giving the same calculated air-flow velocity through each passage. Results of engine-performance tests are presented with variations of power, fuel consumption, explosion pressure, rate of pressure rise, ignition lag, heat loss to the cooling water, and motoring characteristics. For good performance the minimum auxiliary chamber volume, with the cylinder head design used, was 35 per cent of the total clearance volume; for larger volumes the performance improves but slightly. With the auxiliary chamber that contained 35 percent of the clearance volume there were obtained the lowest explosion pressures, medium rates of pressure rise, and slightly less than the maximum power. For all clearance distributions an increase in engine speed decreased the ignition lag in seconds and increased the rate of pressure rise.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TN-435
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  • 54
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    Wind-tunnel Tests of a Hall High-life Wing (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests have been made to find the lift, drag, and center-of-pressure characteristics of a Hall high-lift wing model. The Hall wing is essentially a split-flap airfoil with an internal air passage. Air enters the passage through an opening in the lower surface somewhat back of and parallel to the leading edge, and flows out through an opening made by deflecting the rear portion of the under surface downward as a flap. For ordinary flight conditions the front opening and the rear flap can be closed, providing in effect a conventional airfoil (the Clark Y in this case). The tests were made with various flap settings and with the entrance to the passage both open and closed. The highest lift coefficient found, C(sub L) = 2.08, was obtained with the passage closed.
    Type: NACA-TN-417
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  • 55
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    Influence of several factors on ignition lag in a compression-ignition engine (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made to determine the influence of fuel quality, injection advance angle, injection valve-opening pressure, inlet-air pressure, compression ratio, and engine speed on the time lag of auto-ignition of a Diesel fuel oil in a single-cylinder compression-ignition engine as obtained from an analysis of indicator diagrams. Three cam-operated fuel-injection pumps, two pumps cams, and an automatic injection valve with two different nozzles were used. Ignition lag was considered to be the interval between the start of injection of the fuel as determined with a Stroborama and the start of effective combustion as determined from the indicator diagram, the latter being the point where 4.0 x 10(exp-6) pound of fuel had been effectively burned. For this particular engine and fuel it was found that: (1) for a constant start and the same rate of fuel injection up the point of cut-off, a variation in fuel quantity from 1.2 x 10(exp-4) to 4.1 x 10(exp-4) pound per cycle has no appreciable effect on the ignition lag; (2) injection advance angle increases or decreases the lag according to whether density, temperature, or turbulence has the controlling influence; (3) increase in valve-opening pressure slightly increases the lag; and (4) increase of inlet-air pressure, compression ratio, and engine speed reduces the lag.
    Type: NACA-TN-434
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  • 56
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    Characteristics of two sharp-nosed airfoils having reduced spinning tendencies (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: According to Mr. L.D. Bell, of the Consolidated Aircraft Corporation, certain undesirable spinning characteristics of a commercial airplane were eliminated by the addition of a filler to the forward part of the wing to give it a sharp leading edge. To ascertain what aerodynamic effects result from such a change of section, two airfoils having sharp leading edges were tested in the variable-density wind tunnel. Both sections were derived by modifying the Gott. 398. The tests, which were made at a large value of the Reynolds Number, were carried to very large angles of attack to provide data for application to flight at angles of attack well beyond the stall. The characteristics of the sharp-nosed airfoils are compared with those of the normal Gott. 398 airfoil. Both of the sharp-nosed airfoils, which differ in the angle between the upper and lower surfaces at the leading edge, have about the same characteristics. As compared with the normal airfoil, the maximum lift is reduced by approximately 26 per cent, but the objectionable rapidly decreasing lift with angle of attack beyond the stall is eliminated; the profile drag of the section is slightly reduced in the range of the lift coefficient between 0.2 and 0.85, but at higher and lower lift coefficients the drag is increased.
    Type: NACA-TN-416
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  • 57
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    Drag Tests of 4/9-Scale Model Engine Nacelles with Various Cowlings (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are given of drag tests of 4/9-scale model radial air-cooled engine nacelles made as a part of a general investigation of wing-nacelle-propeller interference. A small nacelle of the type commonly used with exposed engine cylinders was tested with various forms of cowling over the cylinders. The effects of cowling-ring position and of angle of ring chord to the thrust line were investigated. An N.A.C.A. cowled nacelle and a smooth body were also tested. The results are given at 50, 75, and 100 miles per hour for -5 degrees, 0 degrees, 5 degrees, 10 degrees, 15 degrees angle of pitch.
    Type: NACA-TN-432
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  • 58
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    Preliminary investigation of rolling moments obtained with spoilers on both slotted and plain wings (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind-tunnel study has been made to determine the possibility of developing spoilers suitable for providing the lateral control for airplanes in place of the usual ailerons. The first tests were made on a model wing with a fixed tip slot, but when it was found that the effectiveness of the spoilers did not depend to any great extent on the slot, tests were made on a plain wing also. In both cases certain spoiler positions were found which were free from the usual adverse rolling moments with small deflections. Five different forms of spoiler were tested, the best ones being simple plates, either straight or slightly curved to fit the contour of the airfoil when not deflected. Sufficient rolling moment can probably be obtained from spoilers of reasonable size to provide satisfactory lateral control for certain types of airplanes.
    Type: NACA-TN-415
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  • 59
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    Considerations of Air Flow in Combustion Chambers of High-Speed Compression-Ignition Engines (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The air flow in combustion chambers is divided into three fundamental classes - induced, forced, and residual. A generalized resume is given of the present status of air flow investigations and of the work done at this and other laboratories to determine the direction and velocity of air movement in auxiliary and integral combustion chambers. The effects of air flow on engine performance are mentioned to show that although air flow improves the combustion efficiency, considerable induction, friction, and thermal losses must be guarded against.
    Type: NACA-TN-414
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  • 60
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    Flight Tests to Determine the Effect of a Fixed Auxiliary Airfoil on the Lift and Drag of a Parasol Monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Comparative flight tests were made with a small parasol monoplane in which the aerodynamic characteristics of the airplane were determined with the normal wing and with an auxiliary airfoil installed.
    Type: NACA-TN-440
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  • 61
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    Meteorological conditions during the formation of ice on aircraft (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: These are the results of a number of records recently secured from autographic meteorological instruments mounted on airplanes at times when ice formed. Ice is found to collect on an airplane only when the airplane is in some form of visible moisture, such as cloud, fog, mist, rain. etc., and the air temperature is within certain critical limits. Described here are the characteristics of clear ice and rime ice and the specific types of hazards they present to airplanes and lighter than air vehicles. The weather records are classified according to the two general types of formation (clear ice and rime) together with the respective temperatures, relative humidities, clouds, and elevations above ground at which formations occurred. This classification includes 108 cases where rime formed, 43 cases in which clear ice formed, and 4 cases when both rime and clear ice formed during the same flight. It is evident from the above figures that there was a preponderance of rime by the ratio of 2.5 to 1, while in only a few cases both types of ice formation occurred during the same flight.
    Type: NACA-TN-439
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  • 62
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    The compressive strength of duralumin columns of equal angle section (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a chart giving the compressive strength of duralumin columns of equal angle section. The data used in the construction of the chart were obtained from various published sources and were correlated with theory in the range where secondary failure occurred. Appendices are included giving excerpts from Army and Navy specifications for duralumin and approximate formulas for the properties of the equal angle section.
    Type: NACA-TN-413
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  • 63
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    Effect of Engine Operating Conditions on the Vaporization of Safety Fuels (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted with the N.A.C.A. combustion apparatus to determine the effect of compression ratio and engine temperature on the vaporization of a hydrogenated "safety fuel" during the compression stroke under conditions similar to those in a spark-ignition engine. The effects of fuel boiling temperature on vaporization using gasoline, safety fuel, and Diesel fuel oil was also investigated. The results show that increasing the compression ratio has little effect on the rate of fuel vaporization, but that increasing the air temperature by increasing the engine temperature increases the rate of fuel vaporization. The results also show that the vaporized fuel forms a homogeneous mixture with the air more rapidly that does the atomized fuel spray.
    Type: NACA-TN-430
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  • 64
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    Tests on Thrust Augmenters for Jet Propulsion (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This series of tests was undertaken to determine how much the reaction thrust of a jet could be increased by the use of thrust augmenters and thus to give some indication as to the feasibility of jet propulsion for airplanes. The tests were made during the first part of 1927 at the Langley Memorial Aeronautical Laboratory. A compressed air jet was used in connection with a series of annular guides surrounding the jet to act as thrust augmenters. The results show that, although it is possible to increase the thrust of a jet, the increase is not large enough to affect greatly the status of the problem of the application of jet propulsion to airplanes.
    Type: NACA-TN-431
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  • 65
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    The aerodynamic characteristics of airfoils at negative angles of attack (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A number of airfoils, including 14 commonly used airfoils and 10 NACA airfoils, were tested through the negative angle-of-attack range in the NACA variable-density wind tunnel at a Reynolds Number of approximately 3,000,000. The tests were made to supply data to serve as a basis for the structural design of airplanes in the inverted flight condition. In order to make the results immediately available for this purpose they are presented herein in preliminary form, together with results of previous tests of the airfoils at positive angles of attack. An analysis of the results made to find the variation of the ratio of the maximum negative lift coefficient to the maximum positive lift coefficient led to the following conclusions: 1) For airfoils of a given thickness, the ratio -C(sub L max) / +C(sub L max) tends to decrease as the mean camber is increased. 2) For airfoils of a given mean camber, the ratio -C(sub L max) / +C(sub L max) tends to increase as the thickness increases.
    Type: NACA-TN-412
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  • 66
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    Rapid chemical test for the identification of chromium-molybdenum steel (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note describes a simple, rapid, qualitative test which can be applied to solutions of drilling or chips for the identification of chromium-molybdenum steel. The test is based on the orange-red compound which is formed when thiocyanate and inequivalent molybdenum react. This test is much more reliable than the potassium ethylxanthate test which has been recommended for a like purpose. A list of the apparatus and reagents which are required, and a description of the procedure follows.
    Type: NACA-TN-411
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  • 67
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    The Gaseous Explosive Reaction at Constant Pressure : Further Data on the Effect of Inert Gases (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of gaseous explosive reactions is discussed in this report. Measurements were taken to calculate the maximum flame temperature attained and making correlations with existing thermal data on this reaction.
    Type: NACA-TN-438
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  • 68
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    Effect of Aging on Taut Rubber Diaphragms (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of an investigation of special compositions of rubber suitable for use as diaphragms for aircraft instruments, six samples were used as taut diaphragms in instruments and allowed to age for five years. Two of the instruments were in operating condition after this period of time and one had remarkably little change in performance. In making the rubber tetraethyl thorium disulfide was employed as a vulcanizing agent.
    Type: NACA-TN-409
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  • 69
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    Heat Dissipation from a Finned Cylinder at Different Fin-Plane/Air-stream Angles (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives the results of an experimental determination of the temperature distribution in and the heat dissipation from a cylindrical finned surface for various fin-plane/air-stream angles. A steel cylinder 4.5 inches in diameter having slightly tapered fins of 0.30-inch pitch and 0.6 -inch width was equipped with an electrical heating unit furnishing 13 to 248 B.T.U. per hour per square inch of inside wall area. Air at speeds form 30 to 150 miles per hour was directed at seven different angles from 0 degrees to 90 degrees with respect to the fin planes. The tests show the best angle for cooling at all air speeds to be about 45 degrees. With the same temperature for the two conditions and with an air speed of 76 miles per hour, the heat input to the cylinder can be increased 50 percent at 45 degrees fin-plane/air-stream angle over that at 0 degrees.
    Type: NACA-TN-429
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    Experiments on the Distribution of Fuel in Fuel Sprays (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The distribution of the fuel in sprays for compression-ignition engines was investigated by taking high-speed spark photographs of fuel sprays produced under a wide variety of conditions, and also by injecting them against pieces of Plasticine. A photographic study was made of sprays injected into evacuated chambers, into the atmosphere, into compressed air, and into transparent liquids. Pairs of identical sprays were injected counter to each other and their behavior analyzed. Small high-velocity air jets were directed normally to the axes of fuel sprays, with the result that the envelope of spray which usually obscures the core was blown aside, leaving the core exposed on one side.
    Type: NACA-TN-410
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  • 71
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    Preliminary Tests on the Vaporization of Fuel Sprays (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High-speed motion pictures were taken of fuel sprays injected into the combustion chamber of the N.A.C.A. combustion apparatus. Three fuels, ethyl alcohol, gasoline, and fuel oil, which differed considerably in volatility were tested. By maintaining the engine temperature below that required for ignition the spray could be studied from soon after the start of injection until 130 crank degrees later. The results show that the sprays vaporize appreciably so that it is possible for the ignition in high speed compression-ignition engines to take place from the vapor phase.
    Type: NACA-TN-408
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  • 72
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    Characteristics of an Airfoil as Affected by Fabric Sag (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests made at a high value of the Reynolds Number in the N.A.C.A. variable-density wind tunnel to determine the aerodynamic characteristics of an airfoil as affected by fabric sag. Tests were made of two Gottingen 387 airfoils, one having the usual smooth surface and the other having a surface modified to simulate two types of fabric sag. The results of these tests indicate that the usual sagging of the wind covering between ribs has a very small effect on the aerodynamic characteristics of an airfoil.
    Type: NACA-TN-428
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  • 73
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    Effect of the Reservoir Volume on the Discharge Pressures in the Injection System of the N.A.C.A. Spray Photography Equipment (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made to determine the effect of the reservoir volume on the discharge pressures in the injection system of the N.A.C.A. spray photography equipment. The data obtained are applicable to the design of a common rail fuel-injection system. The data show that an injection system of the type described can be designed so that not more than full load fuel quantity can be injected into the engine cylinders, and so that the fuel spray characteristics remain constant over a large range of engine speeds. Formulas are presented for computing the volume of the reservoir and the diameter of the discharge orifice.
    Type: NACA-TN-407
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  • 74
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    The Use of Large Valve Overlap in Scavenging a Supercharged Spark-ignition Engine Using Fuel Injection (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted to determine the effect of more complete scavenging on the full throttle power and the fuel consumption of a four-stroke-cycle engine. The NACA single-cylinder universal test engine equipped with both a fuel-injection system and a carburetor was used. The engine was scavenged by using a large valve overlap and maintaining a pressure in the inlet manifold of 2 inches of mercury above atmospheric. The maximum valve overlap used was 112 degrees. Tests were conducted for a range of compression ratios from 5.5 to 8.5. Except for variable speed tests, all tests were conducted at an engine speed of 1,500 r.p.m. The results of the tests show that the clearance volume of an engine can be scavenged by using a large valve overlap and about 2 to 5 inches of mercury pressure difference between the inlet and exhaust valve. With a fuel-injection system when the clearance volume was scavenged, a b.m.e.p. of over 185 pounds per square inch and a fuel consumption of 9.45 pound per brake horsepower per hour were obtained with a 6.5 compression ratio. An increase of approximately 10 pounds per square inch b.m.e.p. was obtained with a fuel-injection system over that with a carburetor.
    Type: NACA-TN-406
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  • 75
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    Valve timing of engines having intake pressures higher than exhaust (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-405
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  • 76
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    Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 24 (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is the fifth of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests of a group of six low-cambered airfoils in the variable-density wind tunnel. The mean camber lines are identical for the six airfoils and are of such a form that the maximum mean camber is 2 per cent of the chord and is at a position 0.4 of the chord behind the loading edge. The airfoils differ in thickness only, the maximum-thickness/chord ratios being 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results have been presented in the form of both infinite and finite aspect-ratio characteristics. The values of C(sub L) max/C(sub d) degrees min for this group of airfoils are among the highest thus far obtained, the minimum profile drags being approximately equal to those for the symmetrical series of corresponding thickness, while the maximum lift coefficients are considerably higher.
    Type: NACA-TN-404
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  • 77
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    Airplane flight in the stratosphere (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This brief survey of the problems encountered in high-altitude flight deals in particular with the need for high lift coefficient in the wings, large aspect ratios in the wings, and also the problem of hermetically sealing the cabin.
    Type: NACA-TM-660
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  • 78
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    Problems concerning the stability and maneuverability of airplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stability of an airplane can be easily determined by wind-tunnel tests, especially by simple tests with models mounted wind-vane fashion. However, each stability curve plotted by this method is valid only for a certain setting of the corresponding control surface, i.e., it characterizes the stability of the airplane with the control stick in a given position. The problems thus defined are studied from the point of view of longitudinal and transverse stability. Directional stability is not included in this study.
    Type: NACA-TM-663
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  • 79
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    Transmission of heat from a flat plate to a fluid flowing at a high velocity (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The writer, starting with the consideration of the hydrodynamic and thermodynamic equations for the turbulent boundary layer of a flat plate when it is necessary to take into account the heat produced by friction, arrives at the conclusion that the transmission of the heat follows the same law that is valid when the frictional heat is negligible, provided the temperature of the fluid is considered to be that which the fluid would reach if arrested adiabatically. It is then shown how the same law holds good for faired bodies, and some applications of the law are made to the problems of flight at very high speeds.
    Type: NACA-TM-690
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  • 80
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    Increase in the maximum lift of an airplane wing due to a sudden increase in its effective angle of attack resulting from a gust (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests are described, in which the angle of attack of a wing model was suddenly increased (producing the effect of a vertical gust) and the resulting forces were measured. It was found that the maximum lift coefficient increases in proportion to the rate of increase in the angle of attack. This fact is important for the determination of the gust stresses of airplanes with low wing loading. The results of the calculation of the corrective factor are given for a high-performance glider and a light sport plane of conventional type.
    Type: NACA-TM-678
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  • 81
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    The aerodynamic safety of airplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents several hypotheses regarding airplane safety, mainly concerning the nondimensional coefficient of air, speed, acceleration, and wing area on aerodynamic considerations of safety.
    Type: NACA-TM-684
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  • 82
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    The Testing of Airplane Fabrics (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report considers the determining factors in the choice of airplane fabrics, describes the customary methods of testing and reports some of the experimental results. To sum up briefly the results obtained with the different fabrics, it may be said that increasing the strength of covering fabrics by using coarser yarns ordinarily offers no difficulty, because the weight increment from doping is relatively smaller.
    Type: NACA-TM-693
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  • 83
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    Stresses Produced in Airplane Wings by Gusts (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Accurate prediction of gust stress being out of the question because of the multiplicity of the free air movements, the exploration of gust stress is restricted to static method which must be based upon: 1) stress measurements in free flight; 2) check of design specifications of approved type airplanes. With these empirical data the stress must be compared which can be computed for a gust of known intensity and structure. This "maximum gust" then must be so defined as to cover the whole ambit of empiricism and thus serve as prediction for new airplane designs.
    Type: NACA-TM-654
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  • 84
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    Problems Involved in the Choice and Use of Materials in Airplane Construction (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present state of the problem of materials in airplane construction is studied on the basis of data giving the principal characteristics of different materials and showing how they affect the form of airplane parts.
    Type: NACA-TM-658
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  • 85
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    Experiments with planing surfaces (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiments with planing surfaces are fundamental, hydrodynamic researches for the purpose of obtaining the most favorable forms for planing boats, flying boats, and seaplane floats, with respect to water resistance and seaworthiness.
    Type: NACA-TM-661
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  • 86
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    Experimental determination of the thickness of the boundary layer along a wing section (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The thickness and course of the boundary layer were measured in flight, in order to determine whether the relations on an airplane and on a shop-made wing can be brought into agreement with the results of wind-tunnel tests and Horst Muller's calculations of the thickness of the boundary layer, as developed from Karman's integral equation for the boundary layer.
    Type: NACA-TM-679
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  • 87
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    Reduction of wing lift by the drag (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Drag and loss of lift of a wing are attributable to the same cause, wake formation, thus indicating that there is some relation between both. The analysis of measurements on Joukowsky sections revealed a typical course of curves for the interdependence between drag and loss of lift. The shape of the curves apparently depends quite regularly on the mean camber and on the thickness of the profile.
    Type: NACA-TM-681
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  • 88
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    Approximate calculation of multispar cantilever and semicantilever wings with parallel ribs under direct and indirect loading (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method is presented for approximate static calculation, which is based on the customary assumption of rigid ribs, while taking into account the systematic errors in the calculation results due to this arbitrary assumption. The procedure is given in greater detail for semicantilever and cantilever wings with polygonal spar plan form and for wings under direct loading only. The last example illustrates the advantages of the use of influence lines for such wing structures and their practical interpretation.
    Type: NACA-TM-680
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  • 89
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    Maneuverability Investigation of an F6C-4 Fighting Airplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to compare the relative maneuverability of two fighting airplanes and to accumulate additional data to assist in establishing a satisfactory criterion for the maneuverability of any airplane, the National Advisory Committee for Aeronautics has conducted maneuverability investigations on the F6C-3 (water-cooled engine) and the F6C-4 (air-cooled engine) airplanes. The investigation made on the F6C-3 airplane was reported in NACA-TR-369. This report contains the results of the investigation made on the F6C-4 airplane. A comparison of the results with those obtained in the investigation conducted on the F6C-3 airplane shows that: with practically the same speed and control movement, the F6C-4 completed a loop in 10 per cent less time than did F6C-3; in dives, the F6C-3 increased its speed more rapidly than did the F6C-4; and the minimum radius of turn was found to be 135 feet at 61.5 miles per hour for the F6C-4, and 155 feet at 76 miles per hour for the F6C-3.
    Type: NACA-TR-386
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  • 90
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    Wind-Tunnel Tests on Airfoil Boundary Layer Control Using a Backward-Opening Slot (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil. Boundary layer control was accomplished by means of a backward-opening slot in the upper surface of the hollow airfoil. Air was caused to flow through this slot by a pressure which was maintained inside the airfoil by a blower. Various slot locations, slot openings, and wing pressures were used. The tests were conducted in the 5-foot atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory. Under the test conditions, the maximum lift coefficient was increased about 96 per cent for one slot arrangement, and the minimum drag coefficient was decreased about 27 per cent for another, both being compared with the results obtained with the unslotted airfoil. It is believed from this investigation that the above effects may be increased by the use of larger slot openings, better slot locations, multiple slots, improved airfoil profiles, and trailing edge flaps.
    Type: NACA-TR-385
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  • 91
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    The comparative performance of superchargers (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a comparison of superchargers on the basis of the power required to compress the air at a definite rate, and on the basis of the net engine power developed at altitudes from 0 to 40,000 feet. The investigation included geared centrifugal, turbine-driven centrifugal, roots, and vane-type superchargers. It also includes a brief discussion of the mechanical limitations of each supercharger and explains how the method of control affects the power requirements.
    Type: NACA-TR-384
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  • 92
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    Airship Model Tests in the Variable Density Wind Tunnel (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at large Reynolds number.
    Type: NACA-TR-394
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  • 93
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    Hydraulics of Fuel-Injection Pumps for Compression-ignition Engines (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Formulas are derived for computing the instantaneous pressures delivered by a fuel pump. The first derivation considers the compressibility of the fuel and the second, the compressibility, elasticity, and inertia of the fuel. The second derivation follows that given by Sass; it is shown to be the more accurate of the two. Additional formulas are given for determining the resistance losses in the injection tube. Experimental data are presented in support of the analyses. The report is concluded with an application of the theory to the design of fuel pump injection systems for which sample calculations are included.
    Type: NACA-TR-396
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  • 94
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    A New Principle of Sound Frequency Analysis (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In connection with the study of aircraft and propeller noises, the National Advisory Committee for Aeronautics has developed an instrument for sound-frequency analysis which differs fundamentally from previous types, and which, owing to its simplicity of principle, construction, and operation, has proved to be of value in this investigation. The method is based on the well-known fact that the Ohmic loss in an electrical resistance is equal to the sum of the losses of the harmonic components of a complex wave, except for the case in which any two components approach or attain vectorial identity, in which case the Ohmic loss is increased by a definite amount. The principle of frequency analysis has been presented mathematically and a number of distinct advantages relative to previous methods have been pointed out. An automatic recording instrument embodying this principle is described in detail. It employs a beat-frequency oscillator as a source of variable frequency. A large number of experiments have verified the predicted superiority of the method. A number of representative records are presented.
    Type: NACA-TR-395
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  • 95
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    Span-Load Distribution as a Factor in Stability in Roll (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives the results of pressure-distribution tests made to study the effects on lateral stability of changing the span-load distribution on a rectangular monoplane wing model of fairly thick section. Three methods of changing the distribution were employed: variation in profile along the span to a thin symmetrical section at the tip, twist from +5 degrees to -15 degrees at the tip, and sweepback from +20 degrees to -20 degrees. The tests were conducted in a 5-foot closed-throat atmospheric wind tunnel. The investigation shows the following results: (1) change in profile along the span from the NACA-84 at the root to the NACA-M2 at the tip considerably reduces lateral instability, but also reduces the general effectiveness of the wing. (2) washout up to 11 degrees progressively reduces maximum lateral instability. (3) transition from sweepforward to sweepback gradually reduces the useful angle-of-attack range, but has no clearly defined effect on maximum lateral instability.
    Type: NACA-TR-393
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  • 96
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    On the theory of wing sections with particular reference to the lift distribution (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a simple and exact method of calculating the lift distribution on thin wing sections. The most essential feature of the new theory is the introduction of an "ideal angle of attack," this angle being defined as that at which the flow enters the leading edge smoothly or, more precisely, as the angle of attack at which the lift at the leading edge equals zero. The lift distribution at this particular angle is shown to be a characteristic property of the section and has been termed the "basic distribution." it is shown that the lift of a wing section may always be considered to consist of (a) the basic distribution and (b) the additional distribution, where the latter is independent of the mean camber line and thus identical for all thin sections. The specific reason for the poor aerodynamic qualities of thin wing sections is pointed out as being due to the fact that the additional lift in potential flow becomes infinite at the leading edge. It is established that the essential parameter occurring in this analysis is the radius of curvature at the leading edge. It is further established that the actual slope of the lift curve is dependent on this parameter. The theoretical lift distribution is compared with the distribution obtained by direct measurement on a number of the more conventional wing sections. The new theory is of value in calculating the strength of wing sections.
    Type: NACA-TR-383
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  • 97
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    Coefficients of discharge of fuel-injection nozzles for compression-ignition engines (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine the coefficients of discharge of nozzles with small, round orifices of the size used with high-speed compression-ignition engines. The injection pressures and chamber back pressures employed were comparable to those existing in compression-ignition engines during injection. The construction of the nozzles was varied to determine the effect of the nozzle design on the coefficient. Tests were also made with nozzles assembled in an automatic injection valve, both with a plain and with a helically grooved stem. It was found that a smooth passage before the orifice is requisite for high flow efficiency. A beveled leading edge before the orifice gave a higher coefficient of discharge than a rounded edge. The results with the nozzles assembled in an automatic injection valve having a plain stem duplicated those with the nozzles assembled at the end of a straight tube of constant diameter. Lower coefficients were obtained with the nozzles assembled in an injection valve having a helically grooved stem. When the coefficients of nozzles of any one geometrical shape were plotted against values of corresponding Reynold's numbers for the orifice diameters and rates of flow tested, it was found that experimental points were distributed along a single curve.
    Type: NACA-TR-373
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  • 98
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    Dynamic and Flight Tests on Rubber-Cord and Oleo-Rubber-Disk Landing Gears for an F6C-4 Airplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The investigation described in this report was conducted for the purpose of comparing an oleo-rubber-disk and a rubber-cord landing gear, built for use on an F6C-4 airplane. The investigation consisted of drop tests under various loading conditions and flight tests on an F6C-4 airplane. In the drop tests the total work done on each gear and the work done on each of the shock-absorbing units were determined. For both drop tests and flight tests the maximum loads and accelerations were determined. The comparative results showed that the oleo gear was slightly superior in reducing the ordinary landing shocks, that it had a greater capacity for work, and that it was very superior in the reduction of the rebound. The results further showed that for drops comparable to very severe landings, the rubber-cord gear was potentially more effective as a shock-reducing mechanism. However, due to the construction of this chassis, which limited the maximum elongation of the cords, this gear was incapable of withstanding as severe tests as the oleo gear. The action of the oleo gear was greatly inferior to the action of an ideal gear. The maximum accelerations encountered during the flight tests for severe landings were 3.64g for the rubber-cord gear and 2.27g for the oleo gear. These were less than those experienced in free drops of 7 inches on either gear.
    Type: NACA-TR-366
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  • 99
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    The S.A.B.C.A. "S.XI" commercial airplane (Belgian) : a high-wing semicantilever monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-160
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  • 100
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    The Dreieck I Tailless Airplane (German) : A Low-Wing Cantilever Monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-159
    Format: application/pdf
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