ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • Seismology  (8)
  • Aircraft Stability and Control  (7)
  • 1950-1954  (15)
  • 1950  (15)
  • 1
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 2
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 3
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 4
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 5
    facet.materialart.
    Unknown
    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 !
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 6
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 7
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 8
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 9
    facet.materialart.
    Unknown
    Stall Characteristics Obtained from Flight 10 of Northrop X-4 No. 2 Airplane (USAF No. 46-677) (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: NACA instrumentation has been installed ii the X-J4 airplanes to obtain stability and control data during the acceptance tests conducted by the Northrop Aircraft Corporation. This report presents data obtained on the stalling characteristics of the airplane in the clean and gear- down configurations. The center of gravity was located at approximately 18 percent of the mean aerodynamic chord during the tests. The results indicated that the airplane was not completely stalled when stall was gradually approached during nominally U accelerated flight but that it was completely stalled during a more abruptly approached stall in accelerated flight. The stall in accelerated flight was relatively mild, and this was attributed to the nature of the variation of lift with angle of attack for the 001-614 airfoil section, the plan form of the wing, and to the fact that the initial sideslip at the stall produced (as shown by wind-tunnel tests of a model of the airplane) a more symmetrical stall pattern.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-A50A04
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unknown
    Tests of a Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Stability and Control (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents the results of wind-tunnel force tests which were conducted to determine the low-speed stability and control characteristics of a full-scale Northrop XSSM-A-3 missile. Tests were made through a range of angles of attack, sideslip, and control deflection, and at various Reynolds numbers. Characteristics of the complete missile are compared with the characteristics of the missile with the landing skids extended, with the vertical tail removed, and with the fuselage alone. No analysis of the data has been made in order to make the results available as soon as possible.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SA50D05
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 11
    facet.materialart.
    Unknown
    Effect of an Autopilot Sensitive to Yawing Velocity on the Lateral Stability of the Douglas D-558-II Airplane (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A theoretical investigation has been made to determine the effect on the lateral stability of the Douglas D-58-II airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of tire lag in the autopilot were also determined. The flight conditions investigated included landing at sea level, approach condition at 12,000 feet, and cruising at 50,000 feet at Mach numbers of 0.80 and 1.2. The results of the investigation indicated that the lateral stability characteristics of the D-558-II airplane for the flight condition discussed should satisfy the Air Force - Navy period-damping criterion when the proposed autopilot is installed. Airplane motions in sideslip subsequent to a disturbance in sideslip are presented for several representative flight conditions in which a time lag in the autopilot of 0.10 second was assumed.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L50F22
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 12
    facet.materialart.
    Unknown
    Investigations of Lateral Stability of a Glide Bomb Using Automatic Control Having No Time Lag (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The investigation of the lateral stability of an automatically controlled glide bomb led also to the attempt of clarifying the influence of a phugoid oscillation or of any general longitudinal oscillation on the lateral stability of a glide bomb. Under the assumption that its period of oscillation considerably exceeds the rolling and yawing oscillation and that c(sub a) is, at least in sections, practically constant, the result of this test is quite simple. It becomes clear that the influence of the phugoid oscillation may be replaced by suitable variation of the rolling-yawing moment on a rectilinear flight path instead of the phugoid oscillation. If the flying weight of the glide bomb of unchanged dimensions is increased, an increase of the flight velocity will be more favorable than an increase of the lift coefficient. The arrangement of the control permits lateral stability to be achieved in every case; a minimum rolling moment due to sideslip proves of great help.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1248 , ZWB Forschungsbericht; Rept-1819
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 13
    facet.materialart.
    Unknown
    Transonic Stability and Control Investigation of a 1/80-Scale Model of the Consolidated Vultee Skate 9 Seaplane, TED No. NACA DE 345: Transonic-Bump Method (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the longitudinal stability and of the all-movable horizontal tail and aileron control of a 1/80-scale reflection-plane model of the Consolidated Vultee Skate 9 seaplane has been made through a Mach number range of 0.6 to 1.16 on the transonic bump of the Langley high-speed 7- by 10-foot tunnel. At moderate lift coefficients (0.4 to 0.8) and below a Mach number of 1.0 the model was statically unstable longitudinally. The static longitudinal stability of the model at low lift coefficients increased with Mach number corresponding to a shift in aerodynamic center from 37 percent mean aerodynamic chord at a Mach number of 0.60 to 64 percent at a Mach number of 1.10. Estimates indicate that the tail deflection angle required for steady flight and for accelerated maneuvers of the Skate 9 airplane would probably not vary greatly with Mach number at sea level, but for accelerated maneuvers at altitude the tail deflection angle would probably vary erratically with Mach number. The variation of rolling-moment coefficient with aileron deflection angle was approximately linear, agreed well with theory, and held for the range of aileron deflections tested (-17.1 deg to 16.6 deg). At low lift coefficients the drag rise occurred at Mach numbers of 0.95 and 0.90 for the wing alone and the complete model, respectively. The effects of the canopy on the model were small. For the ranges investigated, angle-of-attack and Mach number changes caused no large pressure drops in the jet-engine duct.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL51E22
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 14
    facet.materialart.
    Unknown
    Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363 (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A model of the Convair Y2-2 airplane was tested in Langley tank no. 2 to determine whether satisfactory stability in yawed landings was possible with a certain ventral fin. Free-body landings were made in smooth and rough water at two speeds and two rates of descent with the model yawed 15deg. The behavior of the model was determined by visual observations and from motion-picture re.cords. It was concluded that satisfactory stability was possible with the ventral fin as tested but that the characteristics of the model shock absorbers and the settings of the elevon control surfaces had an appreciable influence on behavior.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL51H17A
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 15
    facet.materialart.
    Unknown
    Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL50A07
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...