75°/45°双三角翼旋涡特性的试验研究

Experimental investigation of the vortex characteristic over 75°/45°double delta wing

采用七孔探针在低速风洞中对双三角翼截面和尾流进行流场测量,并进行翼表面测压试验,研究了75°/45°双三角翼在中等迎角到大迎角下的旋涡特性。试验表明,用七孔探针测量空间流场,结果准确可靠。75°/45°双三角翼的流态特点是,由于内翼涡对外翼涡的诱导作用,使外翼涡趋于稳定,在一定迎角下,两涡发生绕合与合并,随迎角增加,合并涡破裂点前移。

By the measurements of the sectional flowfield over the wing and the wake with sevenhole probe and measurements of pressure distributions on the wing surfaces, a great quantity of experiments in a low speed wind tunnel at high angles of attack have been carried out for studying the vortical interaction of a double delta wing having leading edge sweepback angles of 75°/45°.The experimental results indicate that the measurement of the sectional flowfield by sevenhole probe is reliable. The inducement of the strake vortex has stabilitied the leading vortex. At given angle of attack, the vortices coil round about each other. With increasing angle of attack, the vortex breakdown position moves forward.