Rotor noise is a primary noise source of eVTOLs, and many kinds of computational aeroacoustics have been developed. Wind tunnel testing serves as a crucial means for validating rotor noise computation simulation and reduction designs. In order to supply wind tunnel test data to validate computational aeroacoustics method, research activities on whole-path wind tunnel testing technologies for rotor aerodynamic noise based on an 8-meter-scale large aeroacoustics wind was given in this paper. From the perspective of noise source identification, a 4-meter aperture, 130-channel microphone phased array was developed, along with a rotating sound source identification algorithm based on signal reconstruction. Regarding noise propagation, a low-noise in-flow microphone support structure was designed and a 22-channel scanning U-shaped in-flow microphone array was developed. For near-field noise reception, surface-mounted microphones with embedded installation methods were adopted to achieve acoustic load measurement on aircraft surfaces. In terms of far-field noise reception, a hemispherical far-field noise characterization array was designed to enable high-resolution measurement of noise directivity. A unified data acquisition and processing platform was employed to collect, process, and correct various noise signals. The BO-105 model was utilized to complete whole-path wind tunnel testing verification covering noise source identification, in-flow acoustic propagation, and near/farfield acoustic reception of rotor noise, achieving a seven-time repeatability accuracy of 0.59dB for far-field directivity measurements.