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  • 1
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    Ausfluß aus einer Düse (1940)
    Springer
    Details
    Publication Date: 1940-08-01
    Print ISSN: 0020-1154
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 2
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    Entwurf von Saugrohrkrümmern mit Hilfe der achsensymmetrischen Potentialströmung (1937)
    Springer
    Details
    Publication Date: 1937-01-01
    Print ISSN: 0015-7899
    Electronic ISSN: 1434-0860
    Topics: Technology
    Published by Springer
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    PAPER CURRENT
  • 3
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    The Effect of the Slipstream on an Airplane Wing (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The conditions which must be met at the slipstream boundary are developed, after which it is shown with the aid of the reflection method how these limiting conditions may be complied with in the case of an airfoil in a propeller slipstream in horizontal flow as well as for the propeller in yaw and with allowance for the slipstream rotation. In connection herewith, it is shown how the effective angles of attack and the circulation distribution with due regard to slipstream effect can be predicted and what inferences may be drawn therefrom for the distribution of lift, drag, and pitching moment.
    Type: NACA-TM-920
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    On the theory of hydrofoils and planing surfaces (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present article describes the application of the results of airfoil theory to hydrofoils and planing surfaces with consideration of the boundary conditions of the free upper surface.
    Type: NACA-TM-845
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Impact of a vee-type seaplane on water with reference to elasticity (1936)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The theory developed by H. Wagner for the computation of the landing impact on water for a rigid float is extended to include elastic floats by introducing the concept of an equivalent rigid bottom to substitute for the actual elastic bottom.
    Type: NACA-TM-810
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Measurements on Compressor-Blade Lattices (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: At the end & 1940 an investigation of a guide-vane lattice for the compressor of a TL unit [NACA comment: Turbojet] was requested. The greatest possible Mach number had to be attained. The investigation was conducted with an annular lattice subjected to axial flow. A direct-current shunt motor with a useful output of 235 horsepower at en engine speed of 1800 qm was available for driving the necessary blower. In designing the blower the speed was set at 10,000 rpm. A gear box fran an armored car was used as gearing in which supplementary fresh oil lubrication was installed. The gear box was used to step up from low to high speeds. The blower that was designed is two stage. The hub-tip ratios are 0.79 to 0.82; the design pressure coefficient for each stage is 0.6 and the design flow coefficient is 0.4. The rotor dosimeter D sub a is 0.39 meters and the resulting peripheral speed is u sub a = 204 meters per second [NACA comment: Value corrected from the German]. The blower was entirely satisfactory. The construction of the test stand is shown in figure 1. The air flows in through an annular Inlet, which is used in the measurement of the quantity of air, and is deflected into an inward-pointing radial slot. A spiral motion is imparted to the air by a guide-vane installation manually adjustable as desired, which enables injection of the air, after it has been deflected from the radial direction to the axial direction, into the lattice being investigated at any desired angle.
    Keywords: Mechanical Engineering
    Type: NACA-TM-1193
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight Performance of a Jet Power Plant (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The performance of a jet power plant consisting of a compressor and a turbine is determined by the characteristic curves of these component parts and is controllable by the characteristics of the compressor and the turbine i n relation t o each other. The normal. output, overload, and throttled load of the Jet power plant are obtained on the basis of assumed straight-line characteristics.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1258
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Lift and Drag of Wings with Small Span (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The lift coefficient of!a wing of small span at first shows a linear increase for the increasing angle of attack, but to a lesser degree then was to be expected according to the theory of the lifting line; thereafter the lift coefficient increases more rapidly than linearity, as contrasted with the the theory of the lifting line. The induced drag coefficient for a given lift coefficient, on the other hand, is obviously much smaller than it would be according to the theory. A mall change in the theory of the lifting line will cover these deviations.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1151 , Deutsche Luftfahrtforschung, Forschungsbericht; Rept-1665
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    The Influence of the Diameter Ratio on the Characteristics Diagram of the Axial Compressor (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: With the further development of axial blowers into highly loaded flow machines, the influence of the diameter ratio upon air output and efficiency gains in significance. Clarification of this matter is important for single-stage axial compressors, and is of still greater importance for multistage ones, and particularly for aircraft power plants. Tests with a single-stage axial blower gave a decrease in the attainable maximum pressure coefficient and optimum efficiency as the diameter ratio increased. The decrease must be ascribed chiefly to the guide surface of the hub and housing between the blades increasing with the diameter ratio.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1125
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
    Electronic Resource
    Electronic Resource
    Ausfluß aus einer Düse (1940)
    Springer
    Archive of applied mechanics 11 (1940), S. 264-268 
    Details
    ISSN: 1432-0681
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF02109617
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    Paper (German National Licenses)
    Fulltext
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