通用襟翼模型中冷喷射漩涡的相互作用检测方案(粒子图像测速)

As part of the FARWAKE project, subtask 2.1.1, wake vortex flow experiments are performed using the PIV measurement technique in a water tank. The wake generating model consists of a simple wing/flap model that can be equipped with water jets to simulate propulsion effects. The model was tested at a speed of 3m/s and two angles of attack: 0and 6. Chord Reynolds number of approximately 225.000 and Vortex Reynolds numbers of approximately 150.000 and 220.000 were obtained during the tests. The main objective of the present study is to investigate the influence of a jet on the flap end vortex and the wake vortex formation. The investigation focuses on the direct influence of the jet on the flap end vortex and the (merged) vortex characteristics in the near to mid field. The main vortex characteristics addressed in this report are: the vortex trajectory, the maximum tangential velocity, the peak vorticity and the vortex core radius. The vortex information is obtained from Stereo-PIV experiments performed in a fixed plane perpendicular to the towing direction. The measurements return the 3 components of the velocity in that plane and the streamwise component of the wake vorticity. A submergible moving camera system is used in order to keep the moving vortex in the field of view during the vortex downward motion.