Jie TIAN, Kunyuan ZHANG, Jinglei XU
DOI Number: N/A
Conference number: HiSST-2025-357
Conventional balance force measurement systems are limited to measuring the overall loads and cannot decouple individual component contributions, which restricts the exploration of the flow mechanism behind aerodynamic loads. With the advancement of Particle Image Velocimetry (PIV) technology, a PIV-based aerodynamic load measurement technique has been proposed, which indirectly measures aerodynamic loads by reconstructing multiple physical fields such as pressure and density. However, the performance of conventional pressure field reconstruction methods is severely reduced when applied to supersonic flow fields, which limits the extension of PIV-based aerodynamic load reconstruction method to supersonic nozzles. To address these challenges, this study proposes a supersonic pressure field reconstruction method for supersonic flow and a thrust performance reconstruction measurement for supersonic nozzle based on Flow Vector Splitting (FVS) technology. Through PIV experiments conducted in a direct-connect nozzle wind tunnel, we reconstructed multiphysics fields and aerodynamic performance parameters (including mass flow rate, thrust, and lift) under typical operating conditions. Evaluation results show that the reconstructed data calculated based on FVS method achieves higher accuracy and better self-consistency, satisfying conservation laws of mass flow and momentum. The relative errors of thrust and lift under over expansion conditions are merely -1.70% and 0.60%, respectively. The local errors in post-shock wall pressure remain below 3%. These results outperform conventional Poisson method and spatial integration method. Therefore, the experimental results have verified the feasibility and high accuracy of the PIV-based thrust performance reconstruction methodology for supersonic nozzles, which can provide valuable complementary data to conventional balance force easurement technology.