The report describes the development of the complete stage for the 2. 81 supersonic axial compressor design. The performance of the overall stage including the exit stators and interconnecting duct was evaluated through experimental testing with the rotor and inlet guide vanes developed under the previous phase of this program. The experimental results are analyzed and compared with the design data and criteria for each of the blade rows as well as the overall stage.
Final rept. Jan 1967-Dec 1968
See also Volume 2, AD0857627. DOI: 10.21236/AD0857498