A programme of wind tunnel tests are described with the objective of increasing understanding of the flow physics of 3D transonic wing buffet. The work is part of a larger programme combining numerical simulation and wind tunnel testing. The wind tunnel tests were performed on a half model representative turbulent civil wing design at typical cruise conditions in the Aircraft Research Association 2.74m × 2.44m Transonic Wind Tunnel (TWT). In addition to comprehensive conventional unsteady instrumentation (root strain gauges, accelerometers, pressure transducers), an industrialized Dynamic Pressure-Sensitive Paint (DPSP) system was used to acquire unsteady pressures over the entire upper and lower surface of the wing. This permitted measurement of the detailed development of the shock and separations including progression of the shock structure and shock oscillations. The DPSP revealed that the pressure unsteadiness within a specific frequency range is more important in relation to structural response than standard deviation of the overall unsteady lift coefficient. This may also be important when establishing a relationship between numerical calculations and physical structural response.
展开▼
