Standard Cascade Experiment for Typical High-Load and Large-Turn-Angle Compressor Airfoils (NPU-28))

Reliable and comprehensive compressor cascade test data are essential for establishing high-load compressor design systems and verifying the accuracy of numerical methods. To address the demand for standard cascade test data of high-load compressor blade roots, the absence of authoritative domestic test data, the inadequacy of publicly available data for high-load design needs, and the issue of data misuse due to the lack of flow field quality detection, the National Science and Technology Major Project Group conducted extensive research and discussions. Leveraging the research results from Northwestern Polytechnical University on the influence mechanisms and regulation strategies of planar cascade wind tunnel flow field quality, the independently designed modern high-load compressor standard model cascade NPU-28 (with a blade camber angle of 43.5°, solidity of 1.72, and diffusion factor of 0.5) was established. This study obtained extensive experimental data, including cascade attack angle characteristics, isotropic Mach number on the blade surface, total pressure loss coefficient at the cascade channel exit, and exit flow angle for nine operating conditions within the inflow Mach number range of 0.4 and attack angle range of -10.9° to 5.1°. The data also provide flow field quality parameters, such as inflow Mach number uncertainty, axial velocity density ratio, and exit periodic index, along with measurement positions, test conditions, and inflow turbulence intensity, offering complete test information. Additionally, the data link for the standard blade cascade model NPU-MGS1, based on the DLR compressor Airfoil, is https://www.scidb.cn/s/UbEFZn.