XFOIL Version 6.96 Calculated polar for: GOE 655 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.7321 0.08339 0.08114 -0.0623 1.0000 0.0185 -15.500 -0.8316 0.06418 0.06166 -0.0749 1.0000 0.0183 -15.250 -0.8821 0.05329 0.05060 -0.0823 1.0000 0.0182 -15.000 -0.9161 0.04470 0.04183 -0.0885 1.0000 0.0182 -14.750 -0.9390 0.03766 0.03462 -0.0945 1.0000 0.0183 -14.500 -0.9555 0.03339 0.03020 -0.0971 1.0000 0.0183 -14.250 -0.9833 0.03083 0.02752 -0.0944 1.0000 0.0183 -14.000 -1.0133 0.02996 0.02660 -0.0871 1.0000 0.0184 -13.750 -0.9969 0.02909 0.02563 -0.0869 0.9988 0.0186 -13.500 -0.9794 0.02647 0.02282 -0.0892 0.9957 0.0191 -13.250 -0.9519 0.02543 0.02174 -0.0908 0.9940 0.0195 -13.000 -0.9252 0.02476 0.02104 -0.0916 0.9917 0.0199 -12.750 -0.8975 0.02415 0.02040 -0.0924 0.9893 0.0202 -12.500 -0.8692 0.02344 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0.1975 0.00818 0.00190 -0.0870 0.6207 0.0915 -2.250 0.2218 0.00794 0.00181 -0.0863 0.6066 0.1435 -2.000 0.2468 0.00782 0.00175 -0.0856 0.5913 0.1797 -1.750 0.2720 0.00775 0.00171 -0.0850 0.5752 0.2111 -1.500 0.2971 0.00770 0.00169 -0.0843 0.5587 0.2417 -1.250 0.3223 0.00767 0.00168 -0.0837 0.5420 0.2719 -1.000 0.3474 0.00766 0.00168 -0.0830 0.5244 0.3013 -0.750 0.3724 0.00769 0.00170 -0.0823 0.5051 0.3298 -0.500 0.3972 0.00770 0.00172 -0.0816 0.4856 0.3617 -0.250 0.4217 0.00771 0.00176 -0.0809 0.4667 0.4006 0.000 0.4457 0.00771 0.00181 -0.0801 0.4479 0.4493 0.250 0.4695 0.00770 0.00186 -0.0792 0.4303 0.5021 0.500 0.4922 0.00761 0.00192 -0.0781 0.4142 0.5763 0.750 0.5127 0.00742 0.00201 -0.0765 0.4006 0.6883 1.000 0.5324 0.00727 0.00209 -0.0747 0.3891 0.7875 1.250 0.5545 0.00713 0.00222 -0.0731 0.3786 0.8985 1.500 0.6256 0.00732 0.00240 -0.0825 0.3659 0.9663 2.000 0.7080 0.00768 0.00261 -0.0882 0.3495 0.9923 2.250 0.7501 0.00783 0.00270 -0.0912 0.3430 0.9983 2.500 0.7836 0.00795 0.00277 -0.0925 0.3375 1.0000 2.750 0.8053 0.00810 0.00286 -0.0912 0.3320 1.0000 3.000 0.8279 0.00821 0.00295 -0.0900 0.3282 1.0000 3.250 0.8511 0.00830 0.00302 -0.0890 0.3246 1.0000 3.500 0.8739 0.00842 0.00312 -0.0879 0.3205 1.0000 3.750 0.8963 0.00857 0.00322 -0.0868 0.3167 1.0000 4.000 0.9188 0.00871 0.00334 -0.0856 0.3128 1.0000 4.250 0.9426 0.00880 0.00343 -0.0848 0.3102 1.0000 4.500 0.9660 0.00891 0.00354 -0.0838 0.3070 1.0000 4.750 0.9891 0.00905 0.00365 -0.0828 0.3035 1.0000 5.000 1.0114 0.00922 0.00379 -0.0817 0.2995 1.0000 5.250 1.0346 0.00935 0.00392 -0.0808 0.2960 1.0000 5.500 1.0585 0.00945 0.00403 -0.0800 0.2927 1.0000 5.750 1.0817 0.00958 0.00415 -0.0790 0.2889 1.0000 6.000 1.1040 0.00975 0.00430 -0.0779 0.2847 1.0000 6.250 1.1265 0.00991 0.00445 -0.0769 0.2807 1.0000 6.500 1.1501 0.01002 0.00458 -0.0761 0.2770 1.0000 6.750 1.1727 0.01018 0.00473 -0.0751 0.2721 1.0000 7.000 1.1938 0.01039 0.00491 -0.0738 0.2662 1.0000 7.250 1.2170 0.01052 0.00506 -0.0729 0.2608 1.0000 7.500 1.2375 0.01075 0.00524 -0.0716 0.2520 1.0000 7.750 1.2578 0.01100 0.00544 -0.0703 0.2392 1.0000 8.000 1.2742 0.01135 0.00570 -0.0682 0.2222 1.0000 8.250 1.2885 0.01175 0.00600 -0.0658 0.2044 1.0000 8.500 1.3017 0.01221 0.00637 -0.0632 0.1893 1.0000 8.750 1.3161 0.01265 0.00674 -0.0609 0.1796 1.0000 9.000 1.3328 0.01300 0.00708 -0.0591 0.1737 1.0000 9.250 1.3487 0.01340 0.00747 -0.0572 0.1686 1.0000 9.500 1.3661 0.01375 0.00783 -0.0555 0.1648 1.0000 9.750 1.3846 0.01406 0.00816 -0.0541 0.1622 1.0000 10.000 1.4015 0.01446 0.00856 -0.0525 0.1585 1.0000 10.250 1.4175 0.01490 0.00901 -0.0508 0.1551 1.0000 10.500 1.4332 0.01537 0.00949 -0.0491 0.1516 1.0000 10.750 1.4527 0.01567 0.00983 -0.0480 0.1494 1.0000 11.000 1.4705 0.01606 0.01025 -0.0467 0.1466 1.0000 11.250 1.4860 0.01658 0.01076 -0.0452 0.1427 1.0000 11.500 1.4998 0.01720 0.01139 -0.0435 0.1381 1.0000 11.750 1.5187 0.01757 0.01180 -0.0425 0.1358 1.0000 12.000 1.5350 0.01809 0.01234 -0.0412 0.1312 1.0000 12.250 1.5478 0.01882 0.01305 -0.0396 0.1246 1.0000 12.500 1.5597 0.01963 0.01382 -0.0380 0.1146 1.0000 12.750 1.5632 0.02100 0.01506 -0.0357 0.0948 1.0000 13.000 1.5387 0.02434 0.01811 -0.0312 0.0568 1.0000 13.250 1.5131 0.02821 0.02185 -0.0276 0.0287 1.0000 13.500 1.5049 0.03103 0.02466 -0.0259 0.0197 1.0000 13.750 1.5074 0.03308 0.02677 -0.0249 0.0181 1.0000 14.000 1.5096 0.03522 0.02898 -0.0241 0.0167 1.0000 14.250 1.5120 0.03742 0.03125 -0.0234 0.0160 1.0000 14.500 1.5140 0.03974 0.03364 -0.0229 0.0155 1.0000 14.750 1.5105 0.04271 0.03669 -0.0225 0.0148 1.0000 15.250 1.5064 0.04861 0.04277 -0.0222 0.0139 1.0000 15.500 1.5041 0.05174 0.04599 -0.0223 0.0137 1.0000 15.750 1.5005 0.05509 0.04943 -0.0226 0.0134 1.0000 16.000 1.4943 0.05883 0.05327 -0.0230 0.0131 1.0000 16.250 1.4869 0.06285 0.05739 -0.0235 0.0129 1.0000 16.500 1.4768 0.06730 0.06194 -0.0243 0.0126 1.0000 16.750 1.4650 0.07202 0.06676 -0.0252 0.0124 1.0000 17.000 1.4534 0.07682 0.07167 -0.0263 0.0122 1.0000 17.250 1.4397 0.08198 0.07693 -0.0275 0.0121 1.0000 17.500 1.4199 0.08808 0.08316 -0.0291 0.0119 1.0000 17.750 1.4042 0.09366 0.08884 -0.0305 0.0118 1.0000