XFOIL Version 6.96 Calculated polar for: GIII BL126 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.4666 0.11801 0.11467 -0.0041 1.0000 0.0425 -10.750 -0.4741 0.11415 0.11087 -0.0074 1.0000 0.0432 -10.500 -0.4800 0.11004 0.10678 -0.0101 1.0000 0.0435 -10.250 -0.4841 0.10570 0.10246 -0.0126 1.0000 0.0436 -10.000 -0.4880 0.10109 0.09787 -0.0151 1.0000 0.0437 -9.750 -0.4874 0.09470 0.09149 -0.0133 1.0000 0.0449 -9.500 -0.4796 0.09141 0.08820 -0.0120 1.0000 0.0461 -9.250 -0.4782 0.08757 0.08438 -0.0124 1.0000 0.0472 -9.000 -0.4800 0.08332 0.08015 -0.0135 1.0000 0.0483 -8.750 -0.4843 0.07872 0.07557 -0.0153 1.0000 0.0494 -8.500 -0.4915 0.07374 0.07062 -0.0178 1.0000 0.0503 -8.250 -0.6150 0.07535 0.07200 -0.0226 1.0000 0.0452 -8.000 -0.6088 0.07211 0.06876 -0.0222 1.0000 0.0463 -7.750 -0.6039 0.06852 0.06514 -0.0228 1.0000 0.0476 -7.500 -0.5988 0.06465 0.06116 -0.0237 1.0000 0.0493 -7.250 -0.5927 0.06052 0.05689 -0.0246 1.0000 0.0517 -7.000 -0.5861 0.05839 0.05403 -0.0248 1.0000 0.0561 -6.750 -0.5821 0.05084 0.04658 -0.0250 1.0000 0.0577 -6.500 -0.5686 0.04781 0.04356 -0.0243 1.0000 0.0594 -6.250 -0.5553 0.04498 0.04062 -0.0234 1.0000 0.0621 -6.000 -0.5472 0.04207 0.03704 -0.0211 1.0000 0.0701 -5.750 -0.5398 0.02922 0.02306 -0.0156 1.0000 0.0334 -5.500 -0.5256 0.02782 0.02173 -0.0142 1.0000 0.0363 -5.250 -0.5138 0.02547 0.01904 -0.0114 1.0000 0.0368 -5.000 -0.5012 0.02239 0.01538 -0.0081 1.0000 0.0350 -4.750 -0.4856 0.02059 0.01329 -0.0059 1.0000 0.0353 -4.500 -0.4611 0.01901 0.01151 -0.0054 0.9987 0.0366 -4.250 -0.4229 0.01779 0.01007 -0.0075 0.9947 0.0410 -4.000 -0.3867 0.01635 0.00846 -0.0091 0.9902 0.0446 -3.750 -0.3509 0.01501 0.00715 -0.0110 0.9856 0.0516 -3.500 -0.3139 0.01414 0.00628 -0.0131 0.9810 0.0671 -3.250 -0.2801 0.01312 0.00541 -0.0147 0.9747 0.1022 -3.000 -0.2423 0.01237 0.00490 -0.0173 0.9703 0.1588 -2.750 -0.2112 0.01139 0.00445 -0.0188 0.9636 0.2660 -2.500 -0.1959 0.00942 0.00452 -0.0162 0.9570 0.7608 -2.250 -0.1691 0.00948 0.00468 -0.0147 0.9501 0.8381 -2.000 -0.1395 0.00965 0.00482 -0.0139 0.9440 0.8778 -1.750 -0.1079 0.00983 0.00493 -0.0137 0.9386 0.9033 -1.500 -0.0757 0.01002 0.00503 -0.0137 0.9321 0.9230 -1.250 -0.0362 0.01018 0.00507 -0.0154 0.9279 0.9382 -1.000 0.0088 0.01034 0.00514 -0.0183 0.9233 0.9507 -0.750 0.0659 0.01045 0.00517 -0.0239 0.9206 0.9640 -0.500 0.1247 0.01047 0.00512 -0.0300 0.9177 0.9799 -0.250 0.1625 0.01037 0.00496 -0.0323 0.9102 0.9854 0.000 0.1976 0.01025 0.00480 -0.0340 0.9004 0.9902 0.250 0.2307 0.01014 0.00465 -0.0352 0.8883 0.9953 0.500 0.2655 0.01001 0.00448 -0.0368 0.8757 1.0000 0.750 0.2862 0.00996 0.00440 -0.0355 0.8623 1.0000 1.000 0.3079 0.00993 0.00434 -0.0344 0.8500 1.0000 1.250 0.3305 0.00992 0.00431 -0.0335 0.8392 1.0000 1.500 0.3534 0.00991 0.00428 -0.0327 0.8287 1.0000 1.750 0.3770 0.00992 0.00431 -0.0320 0.8173 1.0000 2.000 0.4006 0.00994 0.00436 -0.0314 0.8062 1.0000 2.250 0.4238 0.00997 0.00441 -0.0305 0.7952 1.0000 2.500 0.4469 0.00999 0.00444 -0.0296 0.7840 1.0000 2.750 0.4699 0.01001 0.00448 -0.0286 0.7720 1.0000 3.000 0.4925 0.01000 0.00450 -0.0274 0.7571 1.0000 3.250 0.5139 0.00990 0.00447 -0.0259 0.7354 1.0000 3.500 0.5354 0.00978 0.00436 -0.0243 0.7109 1.0000 3.750 0.5575 0.00970 0.00430 -0.0228 0.6853 1.0000 4.000 0.5794 0.00966 0.00425 -0.0213 0.6510 1.0000 4.250 0.6002 0.00974 0.00423 -0.0196 0.5979 1.0000 4.500 0.6190 0.01010 0.00426 -0.0176 0.5086 1.0000 4.750 0.6332 0.01104 0.00453 -0.0153 0.3729 1.0000 5.000 0.6467 0.01227 0.00510 -0.0133 0.2410 1.0000 5.250 0.6556 0.01433 0.00616 -0.0108 0.0833 1.0000 5.500 0.6723 0.01553 0.00727 -0.0089 0.0588 1.0000 5.750 0.6900 0.01662 0.00838 -0.0072 0.0491 1.0000 6.000 0.7087 0.01771 0.00947 -0.0056 0.0436 1.0000 6.250 0.7268 0.01937 0.01114 -0.0040 0.0400 1.0000 6.500 0.7490 0.02027 0.01215 -0.0029 0.0360 1.0000 6.750 0.7711 0.02167 0.01361 -0.0019 0.0336 1.0000 7.000 0.7934 0.02355 0.01556 -0.0009 0.0319 1.0000 7.250 0.8156 0.02682 0.01907 0.0000 0.0306 1.0000 7.500 0.8360 0.02853 0.02115 0.0013 0.0288 1.0000 7.750 0.8554 0.03110 0.02409 0.0028 0.0283 1.0000 8.000 0.8711 0.03459 0.02801 0.0045 0.0286 1.0000 8.250 0.8811 0.03971 0.03354 0.0062 0.0297 1.0000 12.250 0.6121 0.12134 0.11806 -0.0007 0.0542 1.0000 12.500 0.6099 0.12685 0.12354 -0.0003 0.0531 1.0000