1. 'fiscous effects may he added to t h ~~ i y. and tble PDjr colIrl has the cdpsbiiity of c.lcu1sting flow solutions f,ov i+r:y Ic_ve! cf vit.(:(jic.'inis:id iterations. The hasic 2-9 bouodary layer method used II tkdl of Uradshaa and Ferriss (ref. 11). To a;ct in simulating three-dimensiondl effects, t.hn w difi c a t i c sof h s h dnd Tseng {ref. 12) for flow about an infinite yswed win> arc appl in.1. The boundary layer displacement thickness, or a portion of it .in var-separated regions, i s added to the basic wing shape at each new inviscic! iteration. B(,undary-layer shape i s then updated with the new pressure distribution. AdCi tional detalls concerning transition location, boundary layer manipuiation in regions or separation,nd the effect of the boundary layer on the boundary condit i n snay b? rwnd in reference 10.
2. By far the most striking change i n flow prediction occurs for the PPW code at the higher Mach number (figs. 4(c) and 4(d)). In the prediction the shock i s moved forward compared to the data by 10-15%. This discrepancy w i l l be discussed later i n this paper.