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  • 1930-1934  (7)
Collection
Keywords
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Years
Year
  • 1
    Electronic Resource
    Electronic Resource
    Reaktionen in flüssigem Ammoniak. I. Sulfide des Germaniums (1934)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 216 (1934), S. 273-287 
    Details
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Germano- und Germanisulfid in kristallisierter Form sind unmittelbar aus Germaniterz gewonnen worden. Die amorphen Formen dieser Sulfide wurden hergestellt. Physikalische und chemische Eigenschaften aller Präparate sind mitgeteilt.
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19342160308
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Reaktionen in flüssigem Ammoniak. I. Sulfide des Germaniums (1934)
    Wiley
    Details
    Publication Date: 1934-01-26
    Print ISSN: 0863-1786
    Topics: Chemistry and Pharmacology
    Published by Wiley
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    PAPER CURRENT
  • 3
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    The aerodynamic analysis of the gyroplane rotating-wing system (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters. Curves of lift-drag ratio against lift coefficient have been calculated for a typical case, showing the effect of varying the pitch angle, the solidarity, and the average blade-section drag coefficient. The analysis expresses satisfactorily the qualitative relations between the rotor characteristics and the rotor parameters. As disclosed by this investigation, the aerodynamic principles of the gyroplane are sound, and further research on this wing system is justified.
    Type: NACA-TN-492
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Simplified aerodynamic analysis of the cyclogiro rotating wing system (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simplified aerodynamic theory of the cyclogiro rotating wing is presented herein. In addition, examples have been calculated showing the effect on the rotor characteristics of varying the design parameters of the rotor. A performance prediction, on the basis of the theory here developed, is appended, showing the performance to be expected of a machine employing this system of sustentation. The aerodynamic principles of the cyclogiro are sound; hovering flight, vertical climb, and a reasonable forward speed may be obtained with a normal expenditure of power. Auto rotation in a gliding descent is available in the event of a power-plant failure.
    Type: NACA-TN-467
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Torsion in box wings (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Logical analysis of a box wing necessitates the allowance for the contribution of the drag spars to the torsional strength of the structure. A rigorous analysis is available in the use of the Method of Least Work. The best logical method of analysis is that applying Prandtl's Membrane Analogy. The results so obtained vary by a negligible amount from those obtained by the rigorous method.
    Type: NACA-TN-366
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A Comparison Between the Theoretical and Measured Longitudinal Stability Characteristics of an Airplane (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report covers an investigation of the application of the theory of dynamic longitudinal stability, based on the assumption of small oscillations, to oscillations an airplane is likely to undergo in flight. The investigation was conducted with a small parasol monoplane for the fixed-stick condition. The period and damping of longitudinal oscillations were determined by direct measurements of oscillations in flight and also by calculation in which the factors that enter the theoretical stability equation were determined in flight. A comparison of the above-mentioned characteristics obtained by these two methods indicates that the theory is applicable to the conditions encountered in flight.
    Type: NACA-TR-442
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Lift and Drag Characteristics and Gliding Performance of an Autogiro as Determined in Flight (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of flight test of the Pitcairn "PCA-2" autogiro. Lift and drag coefficients with the propeller stopped have been determined over approximately a 90 degree range of angles of attack. Based on the sum of fixed-wing and swept-disk areas, the maximum lift coefficient is 0.895, the minimum drag coefficient with propeller stopped is 0.015, and the maximum l/d with propeller stopped is 4.8. Lift coefficients were found also with the propeller delivering positive thrust and did not differ consistently from those found with propeller stopped. Curves of gliding performance included in this report show a minimum vertical velocity of 15 feet per second at an air speed of 36 miles per hour and a flight-path angle of -17 degrees. In vertical descent the vertical velocity is 35 feet per second.
    Type: NACA-TR-434
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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