XFOIL Version 6.94 Calculated polar for: FX 63-100 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6728 0.00901 0.00363 -0.1563 0.7869 0.6995 0.500 0.7270 0.00910 0.00373 -0.1554 0.7687 0.7285 1.000 0.7812 0.00919 0.00383 -0.1546 0.7495 0.7521 1.500 0.8347 0.00927 0.00388 -0.1537 0.7260 0.7756 2.000 0.8869 0.00934 0.00394 -0.1525 0.6989 0.8021 2.500 0.9380 0.00942 0.00407 -0.1511 0.6741 0.8315 3.500 1.0227 0.00960 0.00409 -0.1444 0.5596 1.0000 4.000 1.0656 0.01080 0.00451 -0.1421 0.4322 1.0000 4.500 1.1081 0.01223 0.00527 -0.1402 0.3130 1.0000 5.000 1.1452 0.01433 0.00649 -0.1376 0.1702 1.0000 5.500 1.1836 0.01633 0.00782 -0.1353 0.0712 1.0000 6.000 1.2266 0.01774 0.00899 -0.1335 0.0338 1.0000 6.500 1.2710 0.01889 0.01011 -0.1318 0.0240 1.0000 7.000 1.3155 0.01992 0.01119 -0.1300 0.0165 1.0000 7.500 1.3535 0.02147 0.01272 -0.1273 0.0034 1.0000 8.000 1.3916 0.02283 0.01426 -0.1246 0.0032 1.0000 8.500 1.4242 0.02434 0.01597 -0.1209 0.0032 1.0000 9.000 1.4510 0.02603 0.01788 -0.1165 0.0033 1.0000 9.500 1.4753 0.02796 0.02003 -0.1120 0.0035 1.0000 10.000 1.4964 0.03025 0.02257 -0.1076 0.0036 1.0000 10.500 1.5137 0.03303 0.02562 -0.1033 0.0038 1.0000 11.000 1.5263 0.03643 0.02932 -0.0993 0.0040 1.0000 11.500 1.5325 0.04075 0.03395 -0.0957 0.0042 1.0000 12.000 1.5366 0.04562 0.03910 -0.0930 0.0043 1.0000 12.500 1.5409 0.05091 0.04469 -0.0911 0.0046 1.0000 13.000 1.5367 0.05774 0.05184 -0.0902 0.0048 1.0000 13.500 1.5260 0.06613 0.06055 -0.0905 0.0051 1.0000 14.000 1.5122 0.07581 0.07055 -0.0922 0.0053 1.0000 14.500 1.4968 0.08660 0.08164 -0.0951 0.0055 1.0000 15.500 1.4744 0.10883 0.10455 -0.1036 0.0059 1.0000 16.000 1.4570 0.12225 0.11843 -0.1101 0.0063 1.0000 16.500 1.4356 0.13700 0.13359 -0.1185 0.0064 1.0000 17.000 1.4112 0.15342 0.15041 -0.1289 0.0066 1.0000 17.500 1.3854 0.17124 0.16858 -0.1411 0.0066 1.0000 18.000 1.3598 0.19026 0.18790 -0.1544 0.0065 1.0000 18.500 1.3356 0.21026 0.20810 -0.1683 0.0063 1.0000 19.000 1.3011 0.23670 0.23467 -0.1853 0.0059 1.0000