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Development of a Modular Test Section for Transonic Investigations of Trailing Edge Wake Flows

par Dietz, Andre ;D'Aguanno, Alessandro;Lavagnoli, Sergio
Référence AIAA Paper
Publication Publié, 2026-06-04

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Résumé :

This paper presents the aerodynamic design, fabrication, and numerical validation of a highly modular transonic test section for high-speed aerodynamic research. The primary objective is the investigation of wake flows over a Mach number range of 0.5 to 1.5, with particular focus on unsteady trailing-edge flows, including shock systems and their interactions. Additional applications include boundary layer studies and their influence on vortex shedding. A modular architecture enabled by additive manufacturing allows rapid reconfiguration of geometry and instrumentation, supporting parametric studies under varying flow conditions. To acquire detailed information on boundary layer characteristics and wake behavior, the test section supports a wide range of measurement techniques, including intrusive probes, pressure taps, and optical diagnostics such as Schlieren and particle image velocimetry, as well as thermal methods. A flat-plate configuration provides a baseline, while tailored wall contours enable the imposition of turbine-representative pressure distributions and adverse pressure gradients. In addition, the boundary layer thickness can be controlled through imposed pressure gradients and surface flow control techniques, including air ejection, over a wide range of trailing-edge-to-momentum-thickness ratios from 3.5 to 15. The design combines analytical methods with Reynolds-averaged Navier–Stokes simulations to achieve controlled flow conditions. The presented test section enables independent variation of key flow parameters and provides a modular framework for systematic investigations of transonic wake flows.