Experimental Evaluation of Corner Vanes-Summary 871784
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.
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. Download Citation
Author(s):
Royce Moore, Donald Boldman, Rickey Shyne, Thomas Gelder
Affiliated:
NASA Lewis Research Center
Pages: 20
Event:
Aerospace Technology Conference and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
SAE 1987 Transactions: Aerospace-V96-6
Related Topics:
Wind tunnel tests
Wings
Pressure
Research and development
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