Hybrid laminar flow control experiment on swept wing model

Hybrid laminar flow control(HLFC) was implemented on the symmetry swept wings model using the leading edge suction and favorable pressure gradient.The experiment was operated in a continuous transonic wind tunnel.The effects of Mach number and Reynolds number on transition location were studied.Meanwhile,the effect of leading edge suction flow rates and its distribution on the laminar flow control was analyzed.The wall temperature difference between laminar region and turbulent region was expanded using a wall cooling method in the experiment.The temperature distribution is obtained by the thermocouples embedded in the surface of model,consequently the transition location and the laminar flow region were determined.The results show that there is a good control effectiveness on laminar flow control by the leading edge suction;hence laminar flow area can be significantly expanded.The impacts of the front chamber suction on the laminar flow control are much greater than those of the other.