Closure to “Discussion of ‘A Comparison between Measured and Computed Flow Fields in a Transonic Compressor Rotor’” (1980, ASME J. Eng. Power, 102, pp. 889–890)

Abstract

for a full three-dimensional boundary layer calculation with shock wave interaction. The development of such a complex computational model will require additional laser velocity measurements. These measurements should focus increased attention on the boundary layers and wakes. Data must be acquired on different fans at a variety of operating conditions.