XFOIL Version 6.94 Calculated polar for: FX 83-W-108 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5021 0.00826 0.00265 -0.1249 0.7669 0.4946 0.500 0.5547 0.00824 0.00255 -0.1238 0.7565 0.5015 1.000 0.5977 0.00807 0.00240 -0.1206 0.7347 0.5360 1.500 0.6450 0.00787 0.00251 -0.1184 0.7195 0.6431 3.000 0.8755 0.00751 0.00286 -0.1320 0.6686 1.0000 3.500 0.9197 0.00771 0.00301 -0.1291 0.6412 1.0000 4.000 0.9682 0.00794 0.00323 -0.1276 0.6276 1.0000 4.500 0.9835 0.00887 0.00352 -0.1185 0.4951 1.0000 5.000 1.0131 0.00988 0.00415 -0.1133 0.4107 1.0000 5.500 1.0409 0.01104 0.00487 -0.1081 0.3252 1.0000 6.000 1.0647 0.01256 0.00589 -0.1026 0.2276 1.0000 6.500 1.0961 0.01385 0.00687 -0.0984 0.1614 1.0000 7.000 1.1191 0.01573 0.00812 -0.0931 0.0852 1.0000 7.500 1.1423 0.01761 0.00947 -0.0883 0.0254 1.0000 8.000 1.1891 0.01799 0.01057 -0.0867 0.0665 1.0000 8.500 1.2288 0.01874 0.01112 -0.0851 0.0483 1.0000 9.000 1.2607 0.02015 0.01224 -0.0817 0.0292 1.0000 9.500 1.2875 0.02197 0.01475 -0.0774 0.0434 1.0000 10.000 1.3274 0.02269 0.01495 -0.0764 0.0236 1.0000 10.500 1.3492 0.02500 0.01769 -0.0721 0.0296 1.0000 11.000 1.3573 0.02842 0.02146 -0.0668 0.0295 1.0000 11.500 1.3603 0.03265 0.02597 -0.0612 0.0278 1.0000 12.000 1.4336 0.03050 0.02359 -0.0640 0.0210 1.0000 12.500 1.4544 0.03290 0.02570 -0.0617 0.0104 1.0000 13.000 1.4613 0.03674 0.02968 -0.0578 0.0040 1.0000 13.500 1.4947 0.03820 0.03151 -0.0566 0.0132 1.0000 14.000 1.4997 0.04250 0.03585 -0.0535 0.0054 1.0000 14.500 1.5135 0.04598 0.03973 -0.0516 0.0092 1.0000 15.000 1.4920 0.05356 0.04763 -0.0484 0.0042 1.0000 15.500 1.5140 0.05639 0.05054 -0.0479 0.0050 1.0000 16.500 1.4842 0.07251 0.06735 -0.0473 0.0041 1.0000 17.000 1.4756 0.08045 0.07555 -0.0484 0.0045 1.0000 17.500 1.4608 0.08968 0.08506 -0.0507 0.0042 1.0000 18.000 1.4939 0.09121 0.08665 -0.0510 0.0050 1.0000 18.500 1.4488 0.10574 0.10166 -0.0567 0.0055 1.0000 19.000 1.3061 0.14274 0.13943 -0.0763 0.0037 1.0000 19.500 1.2989 0.15270 0.14953 -0.0822 0.0035 1.0000 20.000 1.2646 0.16946 0.16658 -0.0919 0.0044 1.0000