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<p>This study proposes a novel approach that involves applying the flux vector splitting (FVS) technique to discretize and approximate conservative Navier-Stokes equations and thus reconstruct pressure fields from planar velocimetry data in compressible flows, especially for supersonic flows with strong shocks. Data are typically resolved by using the particle image velocimetry (PIV) technique. Two supersonic experiments under Mach 2.9–3.0 conditions were conducted to generate strong shocks and investigate the performance of the FVS method, including oblique shock flow and shock wave/boundary layer interaction (SWBLI) coupled with flow separation. Reconstructed pressure fields were comprehensively evaluated. The shock polar results indicated that FVS method possessed higher accuracy in post-shock regions with a pressure ratio error of less than 2%, especially for the areas downstream of the shock-shock intersection point and the shock-boundary intersection point, where the conventional Poisson method was ineffective and larger errors accumulated. Wall pressure in SWBLI flow also had better agreement. Furthermore, the performances of different methods were discussed from the perspective of the physical characteristics in supersonic flows, which explained the superiority of the FVS method because the pressure information was delivered along the characteristic direction of physical waves.</p>

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Experimental verification of a PIV-based pressure field reconstruction technology in supersonic flows

  • 期刊论文

  • 发表日期：

    2025年2月14日

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  • Jie Tian,
  • Jinglei Xu,
  • Shun Liu,
  • Le Cai

摘要

This study proposes a novel approach that involves applying the flux vector splitting (FVS) technique to discretize and approximate conservative Navier-Stokes equations and thus reconstruct pressure fields from planar velocimetry data in compressible flows, especially for supersonic flows with strong shocks. Data are typically resolved by using the particle image velocimetry (PIV) technique. Two supersonic experiments under Mach 2.9–3.0 conditions were conducted to generate strong shocks and investigate the performance of the FVS method, including oblique shock flow and shock wave/boundary layer interaction (SWBLI) coupled with flow separation. Reconstructed pressure fields were comprehensively evaluated. The shock polar results indicated that FVS method possessed higher accuracy in post-shock regions with a pressure ratio error of less than 2%, especially for the areas downstream of the shock-shock intersection point and the shock-boundary intersection point, where the conventional Poisson method was ineffective and larger errors accumulated. Wall pressure in SWBLI flow also had better agreement. Furthermore, the performances of different methods were discussed from the perspective of the physical characteristics in supersonic flows, which explained the superiority of the FVS method because the pressure information was delivered along the characteristic direction of physical waves.