Experimental Evaluation of Corner Vanes-Summary

871784

10/01/1987

Event
Aerospace Technology Conference and Exposition
Authors Abstract
Content
Two types of turning vane airfoils (a controlled-diffusion shape and a circular-arc shape) have been evaluated in the high-speed and fan-drive corners of a 0.1-scale model of NASA Lewis Research Center's proposed Altitude Wind Tunnel. The high-speed corner was evaluated with and without a simulated engine exhaust removal scoop. The fan-drive corner was evaluated with and without the high-speed corner. Flow surveys of pressure and flow angle were taken for both the corners and the vanes to determine their respective losses. The two-dimensional vane losses were low; however, the overall corner losses were higher because three-dimensional flow was generated by the complex geometry resulting from intersection of the turning vanes with the end wall. The three-dimensional effects were especially pronounced in the outer region of the circular corner.
Meta TagsDetails
DOI
https://doi.org/10.4271/871784
Pages
20
Citation
Moore, R., Boldman, D., Shyne, R., and Gelder, T., "Experimental Evaluation of Corner Vanes-Summary," SAE Technical Paper 871784, 1987, https://doi.org/10.4271/871784.
Additional Details
Publisher
Published
Oct 1, 1987
Product Code
871784
Content Type
Technical Paper
Language
English