Experimental evaluation of corner vanes - SummaryTwo 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 the turning vanes intersecting the end wall. The three-dimensional effects were especially pronounced in the outer region of the circular corner.
Document ID
19880043551
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Moore, Royce (NASA Lewis Research Center Cleveland, OH, United States)
Boldman, Donald (NASA Lewis Research Center Cleveland, OH, United States)
Shyne, Rickey J. (NASA Lewis Research Center Cleveland, OH, United States)
Gelder, Thomas (NASA Lewis Research Center Cleveland, OH, United States)