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  • Seismology  (19)
  • Aircraft Stability and Control  (17)
  • Aircraft Propulsion and Power  (16)
  • 1940-1944  (52)
  • 1
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    Reflected and minor phases in records of near-by earthquakes in Southern California (1944)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 34, no. 6, pp. 137-160, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Reflectivity ; Nearfield ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Larger shocks of 1942 (deep focus excluded) (1944)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1942, no. 6, pp. 115, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Frequency of earthquakes in California (1944)
    In:  Bull. Seism. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 34, no. 6, pp. 185-188, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Seismicity ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Energy ratio of reflected and refracted seismic waves (1944)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 34, no. 6, pp. 85-102, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Reflectivity ; Energy (of earthquakes) ; Refraction seismics ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Larger shocks of 1941 (deep focus excluded) (1944)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1941, no. 6, pp. 98, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Larger shocks of 1943 (1944)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1943, no. 6, pp. 140, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1944
    Keywords: Seismology ; Earthquake catalog ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    A Theoretical Investigation of Longitudinal Stability of Airplanes with Free Controls Including Effect of Friction in Control System (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The relation between the elevator hinge moment parameters and the control forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance. The stability of the short period oscillations is shown as a series of boundaries giving the limits of the stable regions in terms of the elevator hinge moment parameters. The effects of static stability, elevator moment of inertia, elevator mass unbalance, and airplane density are also considered. Dynamic instability is likely to occur if there is mass unbalance of the elevator control system combined with a small restoring tendency (high aerodynamic balance). This instability can be prevented by a rearrangement of the unbalancing weights which, however, involves an increase of the amount of weight necessary. It can also be prevented by the addition of viscous friction to the elevator control system provided the airplane center of gravity is not behind a certain critical position. For high values of the density parameter, which correspond to high altitudes of flight, the addition of moderate amounts of viscous friction may be destabilizing even when the airplane is statically stable. In this case, increasing the viscous friction makes the oscillation stable again. The condition in which viscous friction causes dynamic instability of a statically stable airplane is limited to a definite range of hinge moment parameters. It is shown that, when viscous friction causes increasing oscillations, solid friction will produce steady oscillations having an amplitude proportional to the amount of friction.
    Keywords: Aircraft Stability and Control
    Type: AD-A301267 , NACA-TR-791
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  • 8
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    NACA Investigation of a Jet-Propulsion System Applicable to Flight (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were sufficiently developed to be considered applicable to flight installation. Calculations indicated that an airplane utilizing this jet-propulsion system would have unusual capabilities in the high-speed range above the speeds of conventional aircraft and would, in addition, have moderately long cruising ranges if only the engine were used.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-528 , NACA-ACR-L4D26
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  • 9
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    Use of Internal Coolant as a Means of Permitting Increase in Engine Take-Off Power (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Engine tests, together with estimates made at Langley Memorial Aeronautical Laboratory, indicate that a 25-percent increase in take-off power can be obtained with present-day aircraft engines without increasing either the knock limit of the fuel or the external cooling requirements of the engine. This increase in power with present fuels and present external cooling is made possible through the use of an internal coolant inducted through the inlet manifold. Estimates on aircraft indicate that this 25-percent increase in power will permit an approximate usable increase of 8.5 percent in the take-off load of existing military airplanes. This increase in load is equivalent to an increase in the weight of gasoline normally carried of between 30 and 65 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-117 , NACA-RB-4A25
    Format: application/pdf
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  • 10
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    Wind Tunnel Investigation of the Effect of Jet-Motor Operation Stability (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of jet-motor operation on the stability and control characteristics of two fighter-type airplanes as determined by wind-tunnel tests of 1/5-scale models are presented. It is shown that the action of the jets is to cause a small loss in stick-fixed stability which is predictable from known theories.
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-A-31
    Format: application/pdf
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  • 11
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    Effects of Propeller Operation and Angle of Yaw on the Distribution of the Load on the Horizontal Tail Surface of a Typical Pursuit Airplane (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-L-227 , NACA-ARR-4B10
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    NASA TECHNICAL REPORTS
  • 12
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    Wind-Tunnel Procedure for Determination of Critical Stability and Control Characteristics of Airplanes (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This report outlines the flight conditions that are usually critical in determining the design of components of an airplane which affect its stability and control characteristics. The wind-tunnel tests necessary to determine the pertinent data for these conditions are indicated, and the methods of computation used to translate these data into characteristics which define the flying qualities of the airplane are illustrated.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-781
    Format: application/pdf
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  • 13
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    An Interim Report on the Stability and Control of Tailless Airplanes (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Problems relating to the stability and control of tailless airplanes are discussed in consideration of contemporary experience and practice.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-796
    Format: application/pdf
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  • 14
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    Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Field measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of fluctuating tail loads in accelerated stalls.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-792
    Format: application/pdf
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  • 15
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    A Theoretical Investigation of Longitudinal Stability of Airplane with Free Controls Including Effect of Friction in Control System (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The relation between the elevator hinge-moment parameters and the control-forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-791
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Comparative Results of Tests on Several Different Types of Nozzles (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This paper presents the results of tests conducted to determine the effect of the constructional elements of a Laval nozzle on the velocity and pressure distribution and the magnitude of the reaction force of the jet. The effect was studied of the shapes of the entrance section of the nozzle and three types of divergent sections: namely, straight cone, conoidal with cylindrical and piece and diffuser obtained computationally by a graphical method due to Professor F. I. Frankle. The effect of the divergence angle of the nozzle on the jet reaction was also investigated. The results of the investigation showed that the shape of the generator of the inner surface of the entrance part of the nozzle essentially has no effect on the character of the flow and on the reaction. The nozzle that was obtained by graphical computation assured the possibility of obtaining a flow for which the velocity of all the gas particles is parallel to the axis of symmetry of the nozzle, the reaction being on the average 2 to 3 percent greater than for the usual conical nozzle under the same conditions, For the conical nozzle the maximum reaction was obtained for a cone angle of 25deg to 27deg. At the end of this paper a sample computation is given by the graphical method. The tests were started at the beginning of 1936 and this paper was written at the same time.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1066 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-478
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  • 17
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    Investigation of Single Stage Axial Fans (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The following investigations are connected with experiments on fans carried out by the author in the Gouttingen Aerodynamic Laboratory within the framework of the preliminary experiments for the new Gouttingen wind-tunnel project. A fan rotor was developed which had very high efficiency at the design point corresponding to moderate pressure and which, in addition, could operate at a proportionally high pressure, rise. To establish the determining operating factors the author carried out extensive theoretical investigation in Hannover. In this it was necessary, to depart from the usual assumption of vanishing radial velocities. The calculations were substantially lightened by the introduction of diagrams. The, first part of the.report describes the theoretical investigations; the second, the experiments carried out at Gouttingen.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1062 , Luftfahyrtforschung; 14; 7; 325-346
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  • 18
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    Determination of the Stresses Produced by the Landing Impact in the Bulkheads of a Seaplane Bottom (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The present report deals with the determination of the impact stresses in the bulkhead floors of a seaplane bottom. The dynamic problem is solved on the assumption of a certain elastic system, the floor being assumed as a weightless elastic beam with concentrated masses at the ends (due to the mass of the float) and with a spring which replaces the elastic action of the keel in the center. The distributed load on the floor is that due to the hydrodynamic force acting over a certain portion of the bottom. The pressure distribution over the width of the float is assumed to follow the Wagner law. The formulas given for the maximum bending moment are derived on the assumption that the keel is relatively elastic, in which case it can be shown that at each instant of time the maximum bending moment is at the point of juncture of the floor with the keel. The bending moment at this point is a function of the half width of the wetted surface c and reaches its maximum value when c is approximately equal to b/2 where b is the half width of the float. In general, however, for computing the bending moment the values of the bending moment at the keel for certain values of c are determined and a curve is drawn. The illustrative sample computation gave for the stresses a result approximately equal to that obtained by the conventional factory computation.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1055 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-449
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    NASA TECHNICAL REPORTS
  • 19
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    The Effect of Piston-Head Temperature on Knock-Limited Power (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: To determine the effect of piston-head temperature on knock-limited power. Tests were made in a supercharged CFR engine over a range of fuel-air ratios from 0.055 to 0.120, using S-3 reference fuel, AN-F-28, Amendment-2, aviation gasoline, and AN-F-28 plus 2 percent xylidines by weight. Tests were run at a compression ratio of 7.0 with inlet-air temperatures of 150 F and 250 F and at a compression ratio of 8.0 with an inlet-air temperature of 250 F. All other engine conditions were held constant. The piston-head temperature was varied by circulation of oil through passages in the crown of a liquid-cooled piston. This method of piston cooling decreased the piston-head temperature about 80 F. The data are not intended to constitute a recommendation as to the advisability of piston cooling in practice.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-35 , NACA-ARR-E4G13
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    NASA TECHNICAL REPORTS
  • 20
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    Compressibility and Heating Effects on Pressure Loss and Cooling of a Baffled Cylinder Barrel (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Theoretical investigations have shown that, because air is compressible, the pressure-drop requirements for cooling an air-cooled engine will be much greater at high altitudes and high speeds than at sea level and low speeds. Tests were conducted by the NACA to obtain some experimental confirmation of the effect of air compressibility on cooling and pressure loss of a baffled cylinder barrel and to evaluate various methods of analysis. The results reported in the present paper are regarded as preliminary to tests on single-cylinder and multi-cylinder engines. Tests were conducted over a wide range of air flows and density altitudes.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-783
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    NASA TECHNICAL REPORTS
  • 21
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    Earthquakes and structure in Southern California (1943)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 54, no. 6, pp. 499-526, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1943
    Keywords: Seismology ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 22
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    Seismological evidence for roots of mountains (1943)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 54, no. 6, pp. 473-498, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1943
    Keywords: Seismology ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 23
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    Recent results of earthquake study in Southern California (1943)
    In:  Trans., Am. Geophys. Union, Milano, Gustav Fischer, vol. 24, no. 6, pp. 95-96, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1943
    Keywords: Seismology ; Seismicity ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 24
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    Antispin-Tail-Parachute Installations (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Although antispin tail parachutes have been used successfully in spin demonstrations for some time, very little published information is available concerning the size of parachute, the bridle-line length, and the type and location of pack to use for particular airplane. The present paper is an attempt to supply data relating to these factors. The paper is in two parts. The first part reviews the principles of operation of the antispin parachutes, views the principles of operation of the antispin parachutes, summarized available information on actual installations, and discusses parachute loads and pack locations. The second part of the paper reports on systematic tests in the NACA-15-foot and 20-foot free-spinning tunnels at the Langley memorial Aeronautical Laboratory to determine the minimum size and the optimum bridle-line lengths for antispin tail parachutes for current military airplanes. It is concluded that airplanes weighing between 7500 and 14,000 pounds require parachutes 8 feet in diameter and bridle-line lengths between 20 and 50 feet. A positive-ejection mechanism is desirable to throw the parachute clear of the tail and to assure rapid opening. The pack and attachment point must be so located that the equipment will not foul the tail surfaces.
    Keywords: Aircraft Stability and Control
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    NASA TECHNICAL REPORTS
  • 25
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    Operating Temperatures of a Sodium-Cooled Exhaust Valve as Measured by a Thermocouple (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A thermocouple was installed in the crown of a sodium-cooled exhaust valve. The valve was then tested in an air-cooled engine cylinder and valve temperatures under various engine operating conditions were determined. A temperature of 1337 F was observed at a fuel-air ratio of 0.064, a brake mean effective pressure of 179 pounds per square inch, and an engine speed of 2000 rpm. Fuel-air ratio was found to have a large influence on valve temperature, but cooling-air pressure and variation in spark advance had little effect. An increase in engine power by change of speed or mean effective pressure increased the valve temperature. It was found that the temperature of the rear spark-plug bushing was not a satisfactory indication of the temperature of the exhaust valve.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-140 , NACA-ARR-3L06
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  • 26
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    The Measurement of Fuel-Air Ratio by Analysis for the Oxidized Exhaust Gas (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy fuel Specification No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene. The method of determining the fuel-air ratio described in this report involves the measurement of the carbon-dioxide content of the oxidized exhaust gas and the use of graphs for the presented equation. This method is considered useful in aircraft, in the field, or in the laboratory for a range of fuel-air ratios from 0.047 to 0.124.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-757
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  • 27
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    Wind-Tunnel Tests of the 1/9-Scale Model of the Curtiss XP-62 Airplane with Various Vertical Tail Arrangements (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of various vertical tail arrangements upon the stability and control characteristics of an XP-62 fighter model was investigated. Rudder-free yaw characteristics with take-off power and flaps deflected were satisfactory after dorsal fin modifications. Directional stability was obtained with all modified vertical tails. Satisfactory rudder effectiveness resulted partly because the dual-rotation propellers produced no asymmetric yawing moments. Pedal forces in sideslips were undesirably large but may be easily reduced.
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-L-779
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  • 28
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    NACA Investigation of a Jet-Propulsion System Applicable to Flight (1943)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made.
    Keywords: Aircraft Propulsion and Power
    Type: NACA/TR-802
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    NASA TECHNICAL REPORTS
  • 29
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    Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been made to determine the motions of and the flight paths describe by a Navy dive-bombing airplane in simulated diving attacks. The data necessary to evaluate these items, with the exception of the atmospheric wind data, were obtained from automatic recording instruments installed entirely within the airplane. The atmospheric wind data were obtained from the ground by the balloon-theodolite method. The results of typical dives at various dive angles are presented in the form of time histories of the motion of the airplane as well as flight paths calculated with respect to still air and with respect to the ground.
    Keywords: Aircraft Stability and Control
    Type: NACA-ACR-248 , NACA-SR-248
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    NASA TECHNICAL REPORTS
  • 30
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    Earthquake magnitude, intensity, energy, and acceleration (1942)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 32, no. 6, pp. 163-192, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1942
    Keywords: Seismology ; Magnitude ; Energy (of earthquakes) ; Intensity ; Strong motions ; BSSA ; FROTH ; (abstract)
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    BIBLIOGRAPHY SEISMOLOGY
  • 31
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    Earthquakes and structure in Southern California (1942)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 53, no. 6, pp. 1818-1819, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1942
    Keywords: Seismology ; Earth model, also for more shallow analyses ! ; CRUST
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    BIBLIOGRAPHY SEISMOLOGY
  • 32
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    Control-Surface Instability on High-Speed Airplanes (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Tests of several modern airplanes indicate that control surfaces with a high degree of aerodynamic balance are likely to possess characteristics which make them unsatisfactory or dangerous in high-speed flight. Dive tests made in the spring of 1940 at the NACA on a naval fighter-type airplane illustrate one form of instability that may be encountered. During a dive at an indicated airspeed of 365 miles per hour, the ailerons suddenly overbalanced. The efforts of the pilot to bring the ailerons back to neutral resulted in a violent oscillation of the control stick from side to side. Fortunately, the force required to return the ailerons to neutral was within the pilot's capabilities. A time history of the maneuver is given in figure1 and typical frames from motion pictures of the cockpit and of the wing, taken during the maneuver, are given in figure 2. In the illustrated case, the occurrence of aerodynamic overbalance was attributed to a slight bulge, approximately 1/16 inch thick, on the lower surface of the leading edges of the ailerons, caused by the installation of additional mass balance ahead of the hinge line. A drawing showing the shape of the bulge is given in figure 3. After this slight protuberance had been eliminated, dives were successfully made at higher speeds.
    Keywords: Aircraft Stability and Control
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    NASA TECHNICAL REPORTS
  • 33
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    Preliminary Investigation Directed Toward Improvement of the NACA Cowling (1942)
    In:  CASI
    Details
    Publication Date: 2018-08-03
    Description: The development of new cowlings, applicable to a short-nose radial engine, is described. These cowlings, designated the NACA cowlings D(sub s) and D(sub sf), employ a larger spinner and a higher inlet-velocity ratio than does the conventional NACA cowling C. The pressures available for cooling and the estimated critical Mach number were found to be higher with the new cowlings than are usually encountered with the conventional NACA cowling C. Large-chord propeller cuffs were found to have a stabilizing effect on the flow entering the cowling and resulted in increased front pressures. Fan blades mounted on the spinner in the inlet opening had a similar effect.
    Keywords: Aircraft Propulsion and Power
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  • 34
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    Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A pursuit type airplane encountered severe diving moments in high-speed dives which make recovery difficult. For the purpose of investigating these diving moments and finding means for their reduction, a 1/6-scale model of the airplane was tested in the 16-foot high-speed wind tunnel at Ames Aeronautical Laboratory. The test results indicate that up to a Mach number of at least 0.75, the limit of the tests, the dive-recovery difficulties can be alleviated and the longitudinal maneuverability improved by the substitution of a long symmetrical fuselage for the standard fuselage.
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-A-65
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  • 35
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    Aerodynamic Heat-Power Engine Operating on a Closed Cycle (1942)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated. A general discussion is given of the experimental installation operating at the Escher Wyss plant in Zurich for a considerable time at high temperatures.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1034 , Zeitschrift des Vereines Deutscher Lagenieure; 85; 22; 491-500
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  • 36
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    Study of Turning Performance of a Fighter-Type Airplane Particularly as Affected by Flaps and Increased Supercharging, Special Report (1942)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Results of a study to determine the effects on turning performance due to various assumed modifications to a typical Naval fighter airplane are presented. The modifications considered included flaps of various types, both part and full space, increased supercharging, and increased wing loading. The calculations indicated that near the low-speed end of the speed range, the turning performance, as defined by steady level turns at a given speed, would be improved to some extent by any of the flaps considered at altitudes up to about 25,000 feet. (If turning is not restricted to the conditions of no loss of speed or altitude, more rapid turning can, of course, be accomplished with the aid of flaps, regardless of altitude.) Fowler flaps and NACA slotted flaps appeared somewhat superior to split or perforated split flaps for maneuvering purposes, particularly if the flap position is not adjustable. Similarly, better turning performance should be realized with full-span than with part-span flaps. Turning performance over the lower half of the speed range would probably not be materially improved at any altitude by increased supercharging of the engine unless the propeller were redesigned to absorb the added power more effectively; with a suitable propeller the turning performance at high altitudes could probably be greatly improved with increased supercharging. A reduction in wing area with the aspect ratio held constant would result in impairment of turning performance over practically the entire speed range at all altitudes.
    Keywords: Aircraft Stability and Control
    Type: NACA-ACR-222 , NACA-SR-222
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  • 37
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    Effects of Direction of Propeller Rotation on the Longitudinal Stability of the 1/10-Scale Model of the North American XB-28 Airplane with Flaps Neutral, Special Report (1942)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The effects of direction of propeller rotation on factors affecting the longitudinal stability of the XB-28 airplane were measured on a 1/10-scale model in the 7- by 10-foot tunnel of the Ames Aeronautical Laboratory. The main effect observed was that caused by regions of high downwash behind the nacelles (power off as well as power on with flaps neutral). The optimum direction of propeller rotation, both propellers rotating up toward the fuselage, shifted this region off the horizontal tail and thus removed its destabilizing effect. Rotating both propellers downward toward the fuselage moved it inboard on the tail and accentuated the effect, while rotating both propellers right hand had an intermediate result. Comparisons are made of the tail effects as measured by force tests with those predicted from the point-by-point downwash and velocity surveys in the region of the tail. These surveys in turn are compared with the results predicted from available theory.
    Keywords: Aircraft Stability and Control
    Type: NACA-ACR-224 , NACA-SR-224
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  • 38
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    Flight Measurements of the Aileron Characteristics of a Grumman F4F-3 Airplane (1942)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The aileron characteristics of a Grumman F4F-3 airplane were determined in flight by means of NACA recording and indicating instruments. The results show that the ailerons met NACA minimum requirements for satisfactory control throughout a limited speed range. A helix angle of approximately 0.07 radian was produced with flaps down at speeds from 90 to 115 miles per hour indicated airspeed and with flaps up from 115 to 200 miles per hour. With flaps up at 90 miles per hour, the helix angle dropped to 0.055 radian; above 200 miles per hour heavy aileron stick forces seriously restricted maneuverability in roll.
    Keywords: Aircraft Stability and Control
    Type: NACA-ACR-239 , NACA-SR-239
    Format: application/pdf
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  • 39
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    Mechanism of faulting in Southern California indicated by seismograms (1941)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 31, no. 6, pp. 263-302, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Tectonics ; Seismicity ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 40
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    Notes of interest (roots of mountains) (1941)
    In:  Earthquake Notes, Milano, Gustav Fischer, vol. 13, no. 6, pp. 4, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Gravimetry, Gravitation
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    BIBLIOGRAPHY SEISMOLOGY
  • 41
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    Seismology (1941)
    Geological Society of America
    In:  Professional Paper, Geology 1888-1938, 50th Anniversary Volume, New York, Geological Society of America, vol. 3, no. VIIa, pp. 438-470, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1941
    Keywords: Review article ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 42
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    Mechanism of faulting in Southern California indicated by seismograms (1941)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 52, no. 6, pp. 1950, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Tectonics ; Seismicity ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 43
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    Seismicity of the earth (1941)
    Geol. Soc. Am.
    In:  New York, 7 + 131 pp., Geol. Soc. Am., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Seismicity ; Review article
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    BIBLIOGRAPHY SEISMOLOGY
  • 44
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    A contribution to the seismic history of Missouri (1941)
    In:  Bull. Seism. Soc. Am., Oxford and Edinburgh, Blackwell Scientific Publications, vol. 31, no. 19, pp. 187-224, pp. 1484, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1941
    Keywords: Seismology ; Seismicity ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 45
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    Wind-tunnel Tests of Four Curtiss Propellers Embodying Different Blade Sections (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests of four 10-foot propellers were made in the propeller-research tunnel for the Army Air Corps to check flight and static thrust test results made on several propellers embodying Clark Y and modified NACA 16-series sections. These propellers were identical as to diameter and activity factor and very closely identical in thickness ratio and pitch distribution. The blades embodied sections with both single- and double-cambered Clark Y, modified NACA 16-series, and a combination of Clark Y and modified NACA-16 airfoils. Tests covered a range of blade angles from 20 deg. to 70 deg., and were all made at tip speeds below 280 feet per second. Although these tests were not conclusive in themselves, owing to the conditions under which they were made, the results seem to check the flight and static tests as closely as would be expected.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-569
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  • 46
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    Flight Tests of the Wilford XOZ-1 Sea Gyroplane (1941)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: During August 1939 a series of flight tests was made at Langley Field on the Wilford sea gyroplane, designated by the Navy as the XOZ-1. These tests were intended to permit rough evaluation of the stability and control characteristics of the machine, with particular reference to possible improvements in rigging which might be made in future machines with fixed wing and nonarticulated feathering control rotor, and to provide data on the bending and feathering motions of the rotor blades. The tests made in 1939 proved inadequate, chiefly because the machine as flown did not have sufficient propeller thrust to give it an appreciable speed range in steady flight. Further tests were therefore made in August 1940 after overhauling the engine and substituting a metal propeller for the wooded one first used. The range of speeds covered in steady flight was markedly extended. Steady-flight runs only were made in this series, since it was felt that takeoffs and landings had been covered sufficiently in the previous tests.
    Keywords: Aircraft Stability and Control
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  • 47
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    Performance Characteristics of an Aircraft Engine with Exhaust Turbine Supercharger, Special Report (1941)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The Pratt and Whitney Aircraft company and the Naval Aircraft Factory of the United States Navy cooperated in a laboratory and flight program of tests on an exhaust turbine supercharger. Two series of dynamometer tests of the engine super-charger combination were completed under simulated altitude conditions. One series of hot gas-chamber tests was conducted by the manufacturer of the supercharger. Flight demonstrations of the supercharger installed in a twin-engine flying boat were terminated by failure of the turbine wheels. The analysis of the results indicated that a two-stage supercharger with the first-stage exhaust turbine driven will deliver rated power for a given indicated power to a higher altitude, will operate more efficiently, and will require simpler controls than a similar engine with the first stage of the supercharger driven from the crankshaft through multispeed gears.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-194
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  • 48
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    Wind-Tunnel Tests of Several Model Tractor-Propeller and Pusher-Propeller Wing Extension-Shaft Arrangements, Special Report (1941)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Tests were made in the 20-foot propeller-research tunnel to investigate the possibility of obtaining increased net efficiencies of propeller-nacelle units by enclosing the engines in the wings and by using extension shafts. A wing of 5-foot chord was fitted with a propeller drive assembly providing for several axial locations of tractor propellers and pusher propellers. A three-blade 4-foot propeller and a three-blade 3 1/2-foot propeller of special design were tested in this wing with spinners and fairings ranging in diameter from 6 to 16 inches. A 16-inch NACA cowling was tested for comparative purposes. Two types of cuffs were also employed. It was found that the net efficiency of a conventional round-shank propeller mounted on an extension shaft in front of or behind a wing increased with an increase in the diameter of the spinner and the shaft housing within the scope of the tests. The largest spinner used had a diameter that might favorably compare with that of a radial engine cowling. The efficiencies for the pusher position appeared to be more critically affected by spinner size than those for the tractor position. The spinners with large diameters for the pusher position resulted in a higher efficiency than those for the corresponding tractor arrangements; the reverse was true for the small spinners. The use of propeller cuffs in combination with a spinner of small diameter generally resulted in net efficiencies that were comparable with those found for the large-spinner combinations.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-196
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  • 49
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    Seismological Tables (1940)
    British Association for the Advancement of Science, Gray Milne Trust
    In:  London, 50 pp., 4th print., 1970, British Association for the Advancement of Science, Gray Milne Trust, vol. 46, no. XVI:, pp. 1-14, (ISBN: 0-387-30752-4)
    Details
    Publication Date: 1940
    Keywords: Earth model, also for more shallow analyses ! ; Travel time ; Seismology ; Handbook of geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 50
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    Deep focus earthquakes in America (1940)
    University of California Press
    In:  Pacific Science Association, 6th Congress Proceedings, vol. 1, Toronto, University of California Press, vol. 10, no. GL-TR-89-0230, pp. 149-150, (ISBN 3-933346-037)
    Details
    Publication Date: 1940
    Keywords: Seismology ; Seismicity ; Hypocentral depth
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  • 51
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    Experimental Determination of Exhaust Gas Thrust, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This investigation presents the results of tests made on a radial engine to determine the thrust that can be obtained from the exhaust gas when discharged from separate stacks and when discharged from the collector ring with various discharge nozzles. The engine was provided with a propeller to absorb the power and was mounted on a test stand equipped with scales for measuring the thrust and engine torque. The results indicate that at full open throttle at sea level, for the engine tested, a gain in thrust horsepower of 18 percent using separate stacks, and 9.5 percent using a collector ring and discharge nozzle, can be expected at an air speed of 550 miles per hour.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-139
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  • 52
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    Flight Tests of Exhaust Gas Jet Propulsion, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Flight test s were conducted on the XP-41 airplane, equipped with a Pratt & Whitney R1830-19, 14-cylinder, air-cooled engine, to determine the increase in flight speed obtainable by the use of individual exhaust stacks directed rearwardly to obtain exhaust-gas thrust. Speed increases up to 18 miles per hour at 20,000 feet altitude were obtained using stacks having an exit area of 3.42 square inches for each cylinder. A slight increase in engine power and decrease in cylinder temperature at a given manifold pressure were obtained with the individual stacks as compared with a collector-ring installation. Exhaust-flame visibility was quite low, particularly in the rich range of fuel-air ratios.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-165
    Format: application/pdf
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