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
  • 1995-1999
  • 1990-1994
  • 1985-1989  (2)
  • 1988  (2)
Collection
Keywords
Years
  • 1995-1999
  • 1990-1994
  • 1985-1989  (2)
Year
  • 1
    facet.materialart.
    Unknown
    Experimental measurements in a large separation bubble due to a simulated glaze ice shape (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effect of a simulated glaze ice accretion on the aerodynamic performance of a NACA 0012 airfoil was studied experimentally. Two ice shapes were tested, one from an experimentally measured accretion and one from an accretion predicted using a computer model given the same icing conditions. Lift, drag and moment coefficients were measured for the airfoil with both ice shapes, smooth and rough. The aerodynamic performance of the two shapes compared well at positive, but not negative, angles of attack. Split hot-film probe velocity data were presented in the upper surface boundary layer and in the wake. Boundary layer parameters were presented for the separation bubble and in the reattached turbulent boundary layer.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 88-0116
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    A flow visualization study of the leading edge separation bubble on a NACA 0012 airfoil with simulated glaze ice (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a part of the ongoing research in aircraft icing, the leading edge separation bubble on the NACA 0012 model with a 5-min simulated glaze ice was investigated. The flow visualization methods used oil, tuft, splitter plate, smoke, and liquid crystals to get reattachment line data for the leading edge separation bubble on both surfaces of the airfoil. On the upper surface, the bubble was found to grow larger with increasing negative angles of attack and reduce in size with increasing angles of attack. The separated flow fails to reattach beyond 6 deg for the upper surface and -5 deg for the lower surface. The results of this study compared well with those of other experiments and computational results.
    Keywords: AERODYNAMICS
    Type: NASA-CR-180846 , NAS 1.26:180846
    Format: text
    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...