有限翼幅の亜音速揚力面理論を検証するに役立つ2次元“DLM-C”

抄録

In order to investigate accuracy and convergence characteristics of any unsteady lifting surface computation programs, it is found that "DLM-C" scheme for two-dimensional airfoils developed by us is quite useful. This scheme is reliable up to high reduced frequencies k and high subsonic free stream Mach numbers M. It has comparable efficiency with NASA 2-D, within the published k and M values. For a rectangular wing of aspect ratio ten chordwise lift distributions on the midspan section are computed by using some unsteady lifting surface programs, which are compared with DLM-C. The values of error-index parameters E are entered in a k vs M diagram, and constant E curves are drawn. This diagram shows clearly the upper limit of k where the scheme is efficient.