The paper presents two-dimensional cascade results which have been obtained in transonic and supersonic cascade windtunnels. The upstream Mach number range is 1,0 ≤ M1 ≤ 1,4. Tests have been carried out with three different blade shapes; these are double-circular-arc and wedge profiles. The influence of solidity on the performance of these cascades has been investigated. A detailed analysis and calculation of the shock losses shows the great influence of profile shape on the total pressure loss coefficient. The profile losses are roughly constant in the investigated Mach number range. In addition, some measurements for different back pressures are presented. These results are analyzed with the aid of a simple calculation, which shows that the axial velocity-density ratio has to be considered as an important parameter in supersonic cascade measurements.
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July 1970
This article was originally published in
Journal of Engineering for Power
Research Papers
Some Experimental Results of Two-Dimensional Compressor Cascades at Supersonic Inlet Velocities
H. Starken,
H. Starken
Deutsche Forschungs- und Versuchsanstalt fu¨r Luft- und Raumfahrt, E. V., Institut fu¨r Luftstrahlantriebe, 505 Porz-Wahn, Germany
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H. J. Lichtfuss
H. J. Lichtfuss
Deutsche Forschungs- und Versuchsanstalt fu¨r Luft- und Raumfahrt, E. V., Institut fu¨r Luftstrahlantriebe, 505 Porz-Wahn, Germany
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H. Starken
Deutsche Forschungs- und Versuchsanstalt fu¨r Luft- und Raumfahrt, E. V., Institut fu¨r Luftstrahlantriebe, 505 Porz-Wahn, Germany
H. J. Lichtfuss
Deutsche Forschungs- und Versuchsanstalt fu¨r Luft- und Raumfahrt, E. V., Institut fu¨r Luftstrahlantriebe, 505 Porz-Wahn, Germany
J. Eng. Power. Jul 1970, 92(3): 267-274 (8 pages)
Published Online: July 1, 1970
Article history
Received:
December 8, 1969
Online:
July 14, 2010
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Citation
Starken, H., and Lichtfuss, H. J. (July 1, 1970). "Some Experimental Results of Two-Dimensional Compressor Cascades at Supersonic Inlet Velocities." ASME. J. Eng. Power. July 1970; 92(3): 267–274. https://doi.org/10.1115/1.3445351
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