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  • Other Sources  (25)
  • Aerodynamics  (15)
  • Seismology  (10)
  • Industrial Chemistry
  • Inorganic Chemistry
  • Mice
  • 2010-2014
  • 1950-1954  (19)
  • 1940-1944  (6)
  • 1950  (19)
  • 1940  (6)
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  • 2010-2014
  • 1950-1954  (19)
  • 1940-1944  (6)
Year
  • 1
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    Das Tibet-Beben vom 15. August 1950 (1950)
    In:  Geologische Rundschau, Milano, California Institute of Technology Pasadena, vol. 38, no. 6, pp. 164, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1950
    Keywords: Seismology ; Earthquake ; Seismicity ; China
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Earthquakes in North America (1950)
    In:  Science, Milano, California Institute of Technology Pasadena, vol. 111, no. 6, pp. 319-324, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1950
    Keywords: Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Wave velocities in the earth's crustal layers (1950)
    In:  Geophysics, Milano, California Institute of Technology Pasadena, vol. 15, no. 6, pp. 156, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1950
    Keywords: Waves ; Velocity analysis ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Progress report, Seismological Laboratory, California Institute of Technology, 1949 (1950)
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 31, no. 3-4, pp. 463-467, pp. 1246
    Details
    Publication Date: 1950
    Keywords: Seismology ; Project report/description ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    An earth model based on a compressibility-pressure hypothesis (1950)
    In:  Monthly Not. R. astr. Soc., Geophys., Tulsa, 3-4, vol. Suppl. 6, no. 1, pp. 50-59, pp. B09405, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1950
    Keywords: Seismology ; D" ; density ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Revised travel time curves for Southern California (1950)
    In:  Bull. Geol. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 61, no. 6, pp. 1546, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1950
    Keywords: Travel time ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Larger shocks of 1949 (1950)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1949, no. 6, pp. 72, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1950
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    The T phase of shallow-focus earthquakes (1950)
    In:  Bull. Seism. Soc. Am., Warszawa, EGS, vol. 40, no. 5, pp. 25-51, pp. B05S16, (ISSN: 1340-4202)
    Details
    Publication Date: 1950
    Keywords: Seismology ; T phase ; Nuclear explosion ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    An Analysis of the Applicability of the Hypersonic Similarity Law to the Study of Flow About Bodies of Revolution at Zero Angle of Attack (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The hypersonic similarity law as derived by Tsien has been investigated by comparing the pressure distributions along bodies of revolution at zero angle of attack. In making these comparisons, particular attention was given to determining the limits of Mach number and fineness ratio for which the similarity law applies. For the purpose of this investigation, pressure distributions determined by the method of characteristics for ogive cylinders for values of Mach numbers and fineness ratios varying from 1.5 to 12 were compared. Pressures on various cones and on cone cylinders were also compared in this study. The pressure distributions presented demonstrate that the hypersonic similarity law is applicable over a wider range of values of Mach numbers and fineness ratios than might be expected from the assumptions made in the derivation. This is significant since within the range of applicability of the law a single pressure distribution exists for all similarly shaped bodies for which the ratio of free-stream Mach number to fineness ratio is constant. Charts are presented for rapid determination of pressure distributions over ogive cylinders for any combination of Mach number and fineness ratio within defined limits.
    Keywords: Aerodynamics
    Type: NACA-TN-2250
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  • 10
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    An Approximate Method of Calculating Pressures in the Tip Region of a Rectangular Wing of Circular-Arc Section at Supersonic Speeds (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-TN-2211
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  • 11
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    Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.90 to 1.95 of 1/14-Scale Model of the Northrop MX-775B Pilotless Aircraft with Small Body (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A flight test was made a t high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a 1/14-scale model of the Northrop MX-775B pilotless aircraft with small small body. The triangular wing of the model had 67.5 deg leading-edge sweep and 15 deg. trailing-edge sweep, The wing airfoil sections were modified NACA 0004 sections. The drag coefficient based on total wing area was 0.0107 at Mach number 1.60. At transonic speeds the maximum drag coefficient was 0.0125. The force-break Mach number was 0,98.
    Keywords: Aerodynamics
    Type: NACA-RM-SL50H18
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  • 12
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    Tests of a Hermes A-2 Missile Body at Mach Number 4.04 (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Force tests on a proposed body shape of the Hermes A-2 missile with and without longitudinal spoilers were made at Mach number 4.04. Values of normal force coefficient, pitching-moment coefficient, and center-of-pressure position were obtained.
    Keywords: Aerodynamics
    Type: NACA-RM-SL50H23A
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  • 13
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    Free-Spinning-Tunnel Investigation of a 1/24-Scale Model of the Grumman AF-2S, -2W Airplane (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman AF-2S, -2W airplane was conducted in the Langley 20-foot free-spinning tunnel. The effects of controls on the erect and inverted spin and recovery characteristics for a range of possible loadings of the.airplane were determined. The effect of a revised-tail installation (small dual fins added to the stabilizer of the original tail and the vertical-tail height of the original tail increased) and the effect of various ventral-fin and antispin-fillet installations were determined. The investigation also included spin-recovery parachute tests.
    Keywords: Aerodynamics
    Type: NACA-RM-SL51B20
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  • 14
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    Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds Several Combinations of the Tail with Each of Two Foreshortened Body Segments (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone.
    Keywords: Aerodynamics
    Type: NACA-RM-SL50G13
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  • 15
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    Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF1OF-1 Airplane (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/30 - scale model of the Grumman XFlOF-1 airplane to determine its spin and recovery characteristics. The investigation included erect and inverted spins for both the straight-wing and swept-wing configurations. Tests to determine the optimum size spin-recovery parachutes and the rudder forces required for recovery were also made. The results indicated that in the straight-wing configuration, satisfactory recoveries of the airplane will be obtained from erect and inverted spins by rudder reversal alone. In the swept-wing configuration recoveries will be unsatisfactory from erect spins. Unsweeping the wings during the spin and reversal of the rudder, however, will lead to eventual recovery. The test results also indicated that, if existing small ailerons are made deflectable through large angles, satisfactory recoveries will be obtained from erect spins in the swept-wing configuration by simultaneous movement of the rudder to against the spin and movement of the ailerons to with the spin. Normal-size ailerons deflected through a normal range would also be effective. Satisfactory recoveries by rudder reversal will be obtained from inverted spins in the swept-wing configuration. In the straight-wing configuration a 14.2-foot tail parachute or a 5.0-foot wing-tip parachute opened on the outer wing tip will effect satisfactory recovery of the airplane by parachute action alone; a 30.0-foot tail parachute or a 10.0-foot wing-tip parachute will be required for the swept-wing configuration. The forces required to fully reverse the rudder should be within the capabilities of the pilot.
    Keywords: Aerodynamics
    Type: NACA-RM-SL50L14
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  • 16
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    Dynamic Response of Control Servo System Installed in NAES-Equipped SB2C-5 Airplane (BuAer No. 83135) (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Dynamic--response measurements for various conditions of displacement and rate signal input, sensitivity setting, and simulated hinge moment were made of the three control-surface servo systems of an NAES-equipped remote-controlled airplane while on the ground. The basic components of the servo systems are those of the General Electric Company type G-1 autopilot using electrical signal. sources, solenoid-operated valves, and hydraulic pistons. The test procedures and difficulties are discussed, Both frequency and transient-response data, are presented and comparisons are made. The constants describing the servo system, the undamped natural frequency, and the damping ratio, are determined by several methods. The response of the system with the addition of airframe rate signal is calculated. The transfer function of the elevator surface, linkage, and cable system is obtained. The agreement between various methods of measurement and calculation is considered very good. The data are complete enough and in such form that they may be used directly with the frequency-response data of an airplane to predict the stability of the autopilot-airplane combination.
    Keywords: Aerodynamics
    Type: NACA-RM-SA50J05
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  • 17
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    Preliminary Performance Data on Westinghouse Electronic Power Regulator Operating on J34-WE-32 Turbojet Engine in Altitude Wind Tunnel (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The behavior of the Westinghouse electronic power regulator operating on a J34-WE-32 turbojet engine was investigated in the NACA Lewis altitude wind tunnel at the request of the Bureau of Aeronautics, Department of the Navy. The object of the program was to determine the, steady-state stability and transient characteristics of the engine under control at various altitudes and ram pressure ratios, without afterburning. Recordings of the response of the following parameters to step changes in power lever position throughout the available operating range of the engine were obtained; ram pressure ratio, compressor-discharge pressure, exhaust-nozzle area, engine speed, turbine-outlet temperature, fuel-valve position, jet thrust, air flow, turbine-discharge pressure, fuel flow, throttle position, and boost-pump pressure. Representative preliminary data showing the actual time response of these variables are presented. These data are presented in the form of reproductions of oscillographic traces.
    Keywords: Aerodynamics
    Type: NACA-RM-SE50J11
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  • 18
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    An Investigation of the Longitudinal Characteristics of the MX-656 Configuration Using Rocket-Propelled Models Preliminary Results at Mach Numbers from 0.65 to 1.25 (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A rocket-propelled model of the Mx-656 configuration has been flown through the Mach number range from 0.65 to 1.25. An analysis of the response of the model to rapid deflections of the horizontal tail gave information on the lift, drag, longitudinal stability and control, and longitudinal-trim change. The lift-coefficient range covered by the test was from -0.2 to 0,3 throughout most of the Mach number range, The model was statically and dynamically stable throughout the lift-coefficient and Mach number range of the test. At subsonic speeds the aerodynamic center moved f o m r d with increasing lift coefficient. The most forward position of the aerodynamic center was about 12,5 percent of the mean aerodynamic chord at a small positive lift coefficient and at a Mach number of about 0.84. A t supersonic speeds the aerodynamic center was well aft, varying from 33 to 39 percent of the mean aerodynamic chord at Mach numbers of 1.0 and 1.25, respectively. Transonic-trim change, as measured by the change in trim lift coefficient with Mach number at a constant t a i l setting, was of small magnitude (about 0.1 lift coefficient for zero tail setting). The zero-lift/drag coefficient increased about 0.042 in the region between a Mach number of 0.9 and 1.1
    Keywords: Aerodynamics
    Type: NACA-RM-SL50J03
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  • 19
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    Investigation of the Model ME 210 in the Spin Wind Tunnel of the DVL (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: After conclusion of the spin investigation of the model Me 210 with elongated fuselage and central vertical tail surfaces (model condition III; reference 3), tests were performed on the same model with a vee tail (model condition IV). Here the entire tail surfaces consist of only one surface with pronounced dihedral. Since the blanketing of the vertical tail surfaces by the horizontal tail surfaces, which may occur in case of standard tail surfaces, does not occur here, one could expect for this type of tail surface favorable spin characteristics, particularly with respect to rudder effectiveness for spin recovery. However, the test results did not confirm these expectations. The steady spin was shown to be very irregular; regarding rudder effectiveness the vee tail surfaces proved to be inferior even to standard tail surfaces, thus they represent the most unfavorable of the four fuselage and tail-surface combinations investigated so far.
    Keywords: Aerodynamics
    Type: NACA-TM-1222 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters (ZWB) Untersuchungen und Mitteilungen; Rept-1288
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  • 20
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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
  • 21
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    Deep focus earthquakes in America (1940)
    University of California Press
    In:  Pacific Science Association, 6th Congress Proceedings, vol. 1, Toronto, University of California Press, vol. 10, no. GL-TR-89-0230, pp. 149-150, (ISBN 3-933346-037)
    Details
    Publication Date: 1940
    Keywords: Seismology ; Seismicity ; Hypocentral depth
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    BIBLIOGRAPHY SEISMOLOGY
  • 22
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    Wind-tunnel Tests of the NACA 45-125 Airfoil: A Thick Airfoil for High-Speed Airplanes (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Investigations of the pressure distribution, the profile drag, and the location of transition for a 30-inch-chord 25-percent-thick N.A,C.A. 45-125 airfoil were made in the N.A.C.A 8-foot high-speed wind tunnel for the purpose of aiding in the development of a thick wing for high-speed airplanes. The tests were made at a lift coefficient of 0.1 for Reynolds Numbers from 1,750,000 to 8,690,000, corresponding to speeds from 80 to 440 miles per hour at 59 F. The effect on the profile drag of fixing the transition point was also investigated. The effect of compressibility on the rate of increase of pressure coefficients was found to be greater than that predicted by a simplified theoretical expression for thin wings. The results indicated that, for a lift coefficient of 0.1, the critical speed of the N.A.C,A. 45-125 airfoil was about 460 miles per hour at 59 F,. The value of the profile-drag coefficient at a Reynolds Number of 4,500,000 was 0.0058, or about half as large as the value for the N.A,C,A. 0025 airfoil. The increase in the profile-drag coefficient for a given movement of the transition point was about three times as large as the corresponding increase for the N.A.C,A. 0012 airfoil. Transition determinations indicated that, for Reynolds Numbers up to ?,000,000, laminar boundary 1ayers were maintained over approximately 40 percent of the upper and the lower surfaces of the airfoil.
    Keywords: Aerodynamics
    Type: NACA-SR-138
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  • 23
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    Wind-Tunnel Investigation of the Lift Characteristics of an NACA 27-212 Airfoil Equipped with Two Types of Flap, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 27-212 airfoil with a 20% chord split flap and with two arrangements of a 25.66% chord slotted flap to determine the section lift characteristics as affected by flap deflection for the split flap and as affected by flap deflection, flap position, and slot shape for the slotted flap. For the two arrangements of the slotted flap, the flap positions for maximum section lift are given. Comparable data on the NACA 23012 airfoil equipped with similar flaps are also given. On the basis of maximum section lift coefficient, the slotted flap with an easy slot entry was slightly better than either the split flap or the slotted flap with a sharp slot entry. With both types of flap the decrease in the angle of attack, for maximum section lift coefficient, with flap deflection is large for the NACA 27-212 airfoil as compared with the NACA 23012 airfoil. Also with both flaps, the maximum section lift coefficient obtained with flaps is much lower for the NACA 27-212 airfoil than for the NACA 23012 airfoil.
    Keywords: Aerodynamics
    Type: NACA-SR-159
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  • 24
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    Full-Scale Tests of Several Propellers Equipped with Spinners, Cuffs, Airfoil and Round Shanks, and NACA 16-Series Sections, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of several propeller, cuff, and spinner combinations were conducted in the 20 foot propeller-research tunnel. Three propellers, which ranged in diameter from 8.4 to 11.25 feet, were tested at the front end of a streamline body incorporating spinners of two diameters. The tests covered a blade angle range from 20 deg to 65 deg. The effect of spinner diameter and propeller cuffs on the characteristics of one propeller was determined. Test were also conducted using a propeller which incorporated aerodynamically good shank sections and using one which incorporated the NACA 16 series sections for the outer 20 percent of the blades. Compressibility effects were not measured, owing to the low testing speeds. The results indicated that a conventional propeller was slightly more efficient when tested in conjunction with a 28 inch diameter spinner than with a 23 inch spinner, and that cuffs increased the efficiency as well as the power absorption characteristics. A propeller having good aerodynamic shanks was found to be definitely superior from the efficiency standpoint to a conventional round-shank propeller with or without cuffs; this propeller would probably be considered structurally impracticable, however. The propeller incorporating the NACA 16 series sections at the tims were found to have a slightly higher efficiency than a conventional propeller; the take-off characteristics appeared to be equally good. The effects noted above probably would be accentuated at helical speeds at which compressibility effects would enter.
    Keywords: Aerodynamics
    Type: NACA-SR-168
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  • 25
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    Boundary-Layer Transition on the N.A.C.A. 0012 and 23012 Airfoils in the 8-Foot High-Speed Wind Tunnel, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Determinations of boundary-layer transition on the NACA 0012 and 2301 airfoils were made in the 8-foot high-speed wind tunnel over a range of Reynolds Numbers from 1,600,000 to 16,800,000. The results are of particular significance as compared with flight tests and tests in wind tunnels of appreciable turbulence because of the extremely low turbulence in the high-speed tunnel. A comparison of the results obtained on NACA 0012 airfoils of 2-foot and 5-foot chord at the same Reynolds Number permitted an evaluation of the effect of compressibility on transition. The local skin friction along the surface of the NACA 0012 airfoil was measured at a Reynolds Number of 10,000,000. For all the lift coefficient at which tests were made, transition occurred in the region of estimated laminar separation at the low Reynolds Numbers and approach the point of minimum static pressure as a forward limit at the high Reynolds Numbers. The effect of compressibility on transition was slight. None of the usual parameters describing the local conditions in the boundary layer near the transition point served as an index for locating the transition point. As a consequence of the lower turbulence in the 8-foot high-speed tunnel, the transition points occurred consistently farther back along the chord than those measured in the NACA full-scale tunnel. An empirical relation for estimating the location of the transition point for conventional airfoils on the basis of static-pressure distribution and Reynolds Number is presented.
    Keywords: Aerodynamics
    Type: NACA-SR-137
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