Print Email Facebook Twitter Surface pressure and aerodynamic loads determination of a transonic airfoil based on particle image velocimetry Title Surface pressure and aerodynamic loads determination of a transonic airfoil based on particle image velocimetry Author Ragni, D. Ashok, A. van Oudheusden, B.W. Scarano, F. Faculty Aerospace Engineering Date 2009-12-31 Abstract The present investigation assesses a procedure to extract the aerodynamic loads and pressure distribution on an airfoil in the transonic flow regime from particle image velocimetry (PIV) measurements. The wind tunnel model is a two-dimensional NACA-0012 airfoil, and the PIV velocity data are used to evaluate pressure fields, whereas lift and drag coefficients are inferred from the evaluation of momentum contour and wake integrals. The PIV-based results are compared to those derived from conventional loads determination procedures involving surface pressure transducers and a wake rake. The method applied in this investigation is an extension to the compressible flow regime of that considered by van Oudheusden et al (2006 Non-intrusive load characterization of an airfoil using PIV Exp. Fluids 40 988–92) at low speed conditions. The application of a high-speed imaging system allows the acquisition in relatively short time of a sufficient ensemble size to compute converged velocity statistics, further translated in turbulent fluctuations included in the pressure and loads calculation, notwithstanding their verified negligible influence in the computation. Measurements are performed at varying spatial resolution to optimize the loads determination in the wake region and around the airfoil, further allowing us to assess the influence of spatial resolution in the proposed procedure. Specific interest is given to the comparisons between the PIV-based method and the conventional procedures for determining the pressure coefficient on the surface, the drag and lift coefficients at different angles of attack. Results are presented for the experiments at a free-stream Mach number M = 0.6, with the angle of attack ranging from 0? to 8?. Subject PIVaerodynamic loads measurementtransonic airfoil To reference this document use: http://resolver.tudelft.nl/uuid:b764abb1-6fe1-4f51-a709-b9e9aa5cf80a Publisher IOP ISSN 0957-0233 Source Measurement science & technology, 20(7)2009 Part of collection Institutional Repository Document type journal article Rights (c) 2009 Ragni, D.; Ashok, A. Van Oudheusden, B.W.; Scarano, F. Files PDF 233564.pdf 2.23 MB Close viewer /islandora/object/uuid:b764abb1-6fe1-4f51-a709-b9e9aa5cf80a/datastream/OBJ/view