DBD-PAの小型航空機適用に向けた片翼模型の風洞試験

抄録

For installation of a dielectric-barrier-discharge plasma actuator (DBD-PA) on a small fixed-wing UAV, a wind-tunnel experiment using a NACA23015 three-dimensional wing model with a chord-length of 200 mm and an aspect ratio of 3.5 was conducted. The chord-based Reynolds number was set to 126,000. The flow-control capability was evaluated by time-averaged pressure measurement. Under this condition, a stall occurred around an angle of attack of 13 degrees, and flow-control experiments with a DBD-PA were conducted at an angle of attack of 19 degrees as a deep-stall angle and the capability of flow control was evaluated with changing the span-wise DBD-PA length. Results show that the flow-control capability is almost unchanged from the span-wise DBD-PA length of 80 % to 92 % (the maximum length in this experiment), and decreases abruptly at the whole span region below the length of 80 %, rather than changes linearly. This result is important knowledge for the installation of DBD-PA on a fixed-wing UAV.