亜音速非定常揚力面計算法（ＢＩＳ） ＩＩ 数値計算結果

Abstract

This paper concerns with numerical evaluation of a new computation method for unsteady subsonic lifting surfaces, BIS (Box-In-Strip), the formulation of which was reported minutely in our previous paper. The numerical results of BIS-QS, a refined version, are compared with those of DLM (DoubletLattice Method) and DPM (Doublet-Point Method). Three kinds of wing planform, designated as Wing R, H, and E are used for evaluating these schemes. A new criterion is used on Wing R (rectangular planform); comparison is made between the pressure distribution at the root chord of a high aspect ratio wing and that of 2-dimensional airfoils, besides the "Error-Index" is used which has been developed by our laboratory previously. The Wing H has leading and trailing edges of a smooth hyperbolic curve, while the Wing E has a swept-tapered planform and so a kink at the midspan. It is found that the convergence and accuracy of BIS-QS are superior to DLM significantly and to DPM remarkably, without increasing computation cost, even for high frequency and high subsonic Mach number.