可撓面をもつ細長三角翼の前縁はく離流れ

抄録

The main feature of the flow past a slender delta wing is the existence of leading-edge separation. It has been shown in many investigations that this separation greatly contributes the wing performance. But no papers exist about a slender parawing with leading-edge separation. In the present paper, the flow over a slender one-lobed parawing with leading-edge separation is considered by using the simple model of BROWN and MICHAEL and the slender body theory, assuming the flow field to be conical.
Wing shape, vortex position and strength can be found from a set of non-linear simultaneous equations which describe the stream surface condition of the wing and the statical balance between the surface tension and the pressure jump through the wing, together with the zeroforce condition on the vortex system. The solutions are obtained for various values ofλand K, i.e. the wing tension and the incidence parameter, respectively, by making use of NEWTON-RAPHSON's numerical procedure. Normal force and pressure distribution are also calculated from the values that specify the wing shape, the vortex position and strength.
It is shown that the wing shape is a little different from the attached flow solution because of high negative pressure on the upper surface caused by a separation vortex and that the maximum normal force occurs at a certain value of λin the case where K is large.