XFOIL Version 6.96 Calculated polar for: GOE 676 (= M 12) 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.5197 0.11240 0.10870 -0.0142 1.0000 0.0683 -10.500 -0.5460 0.10456 0.10094 -0.0256 1.0000 0.0696 -10.250 -0.5658 0.09618 0.09258 -0.0355 1.0000 0.0698 -10.000 -0.5342 0.09626 0.09266 -0.0235 1.0000 0.0717 -9.750 -0.5243 0.09378 0.09019 -0.0227 1.0000 0.0730 -9.500 -0.5206 0.09033 0.08674 -0.0238 1.0000 0.0746 -9.250 -0.5227 0.08584 0.08228 -0.0266 1.0000 0.0766 -9.000 -0.5353 0.07937 0.07586 -0.0329 1.0000 0.0784 -8.750 -0.5627 0.07267 0.06912 -0.0383 1.0000 0.0800 -8.500 -0.5424 0.05514 0.05161 -0.0438 1.0000 0.0844 -8.250 -0.5163 0.05388 0.05048 -0.0424 1.0000 0.0866 -8.000 -0.5216 0.05108 0.04767 -0.0403 1.0000 0.0884 -7.750 -0.5360 0.04814 0.04469 -0.0371 1.0000 0.0900 -7.500 -0.5551 0.04561 0.04209 -0.0328 1.0000 0.0918 -7.250 -0.6043 0.04582 0.04170 -0.0243 1.0000 0.0964 -7.000 -0.6413 0.04003 0.03484 -0.0223 1.0000 0.0666 -6.750 -0.6421 0.03633 0.03081 -0.0186 1.0000 0.0644 -6.500 -0.6338 0.03333 0.02743 -0.0161 0.9994 0.0642 -6.250 -0.6024 0.02961 0.02316 -0.0177 0.9953 0.0640 -6.000 -0.5686 0.02703 0.02015 -0.0194 0.9910 0.0647 -5.750 -0.5327 0.02530 0.01809 -0.0214 0.9864 0.0668 -5.500 -0.4937 0.02367 0.01611 -0.0237 0.9830 0.0682 -5.250 -0.4583 0.02253 0.01469 -0.0253 0.9770 0.0694 -5.000 -0.4206 0.02051 0.01255 -0.0276 0.9731 0.0722 -4.750 -0.3789 0.01947 0.01149 -0.0307 0.9702 0.0755 -4.500 -0.3437 0.01859 0.01054 -0.0322 0.9633 0.0784 -4.250 -0.3019 0.01779 0.00964 -0.0349 0.9591 0.0819 -4.000 -0.2607 0.01661 0.00852 -0.0378 0.9559 0.0877 -3.750 -0.2287 0.01600 0.00793 -0.0386 0.9468 0.0936 -3.500 -0.1916 0.01516 0.00714 -0.0405 0.9414 0.1012 -3.250 -0.1625 0.01473 0.00671 -0.0406 0.9307 0.1111 -3.000 -0.1321 0.01422 0.00626 -0.0409 0.9218 0.1253 -2.750 -0.1057 0.01363 0.00580 -0.0403 0.9111 0.1458 -2.500 -0.0830 0.01296 0.00535 -0.0392 0.8987 0.1895 -2.250 -0.0691 0.01142 0.00494 -0.0368 0.8864 0.4315 -2.000 -0.0582 0.01016 0.00492 -0.0324 0.8753 0.7202 -1.750 -0.0331 0.01017 0.00523 -0.0299 0.8640 0.8472 -1.500 -0.0072 0.01037 0.00538 -0.0281 0.8517 0.8930 -1.250 0.0234 0.01060 0.00551 -0.0274 0.8405 0.9205 -1.000 0.0630 0.01087 0.00565 -0.0286 0.8305 0.9415 -0.750 0.1249 0.01120 0.00586 -0.0346 0.8194 0.9602 -0.500 0.1811 0.01135 0.00587 -0.0398 0.8085 0.9758 -0.250 0.2386 0.01135 0.00572 -0.0456 0.7977 0.9902 0.000 0.2917 0.01122 0.00551 -0.0510 0.7843 1.0000 0.250 0.3157 0.01115 0.00535 -0.0504 0.7708 1.0000 0.500 0.3399 0.01109 0.00521 -0.0499 0.7578 1.0000 0.750 0.3641 0.01104 0.00508 -0.0493 0.7451 1.0000 1.000 0.3884 0.01100 0.00494 -0.0487 0.7327 1.0000 1.250 0.4130 0.01096 0.00485 -0.0482 0.7196 1.0000 1.500 0.4376 0.01095 0.00478 -0.0477 0.7059 1.0000 1.750 0.4621 0.01094 0.00470 -0.0471 0.6911 1.0000 2.000 0.4865 0.01095 0.00463 -0.0464 0.6756 1.0000 2.250 0.5110 0.01098 0.00458 -0.0458 0.6598 1.0000 2.500 0.5354 0.01104 0.00456 -0.0451 0.6442 1.0000 2.750 0.5600 0.01112 0.00460 -0.0445 0.6293 1.0000 3.000 0.5843 0.01122 0.00465 -0.0439 0.6147 1.0000 3.250 0.6083 0.01133 0.00471 -0.0432 0.5996 1.0000 3.500 0.6320 0.01145 0.00479 -0.0424 0.5835 1.0000 3.750 0.6555 0.01156 0.00487 -0.0417 0.5673 1.0000 4.000 0.6788 0.01169 0.00496 -0.0408 0.5511 1.0000 4.250 0.7020 0.01182 0.00507 -0.0399 0.5350 1.0000 4.500 0.7247 0.01196 0.00518 -0.0390 0.5181 1.0000 4.750 0.7473 0.01212 0.00531 -0.0380 0.5015 1.0000 5.000 0.7698 0.01230 0.00547 -0.0370 0.4864 1.0000 5.250 0.7920 0.01250 0.00565 -0.0360 0.4706 1.0000 5.500 0.8139 0.01272 0.00584 -0.0349 0.4552 1.0000 5.750 0.8358 0.01296 0.00607 -0.0338 0.4411 1.0000 6.000 0.8574 0.01321 0.00633 -0.0327 0.4269 1.0000 6.250 0.8785 0.01348 0.00658 -0.0315 0.4109 1.0000 6.500 0.8990 0.01375 0.00683 -0.0302 0.3930 1.0000 6.750 0.9190 0.01405 0.00709 -0.0288 0.3742 1.0000 7.000 0.9387 0.01434 0.00740 -0.0274 0.3527 1.0000 7.250 0.9572 0.01470 0.00769 -0.0258 0.3278 1.0000 7.500 0.9756 0.01508 0.00804 -0.0242 0.2989 1.0000 7.750 0.9928 0.01559 0.00845 -0.0225 0.2632 1.0000 8.000 1.0080 0.01628 0.00896 -0.0207 0.2183 1.0000 8.250 1.0220 0.01714 0.00960 -0.0187 0.1812 1.0000 8.500 1.0366 0.01801 0.01032 -0.0169 0.1578 1.0000 8.750 1.0508 0.01890 0.01112 -0.0150 0.1399 1.0000 9.000 1.0631 0.01991 0.01206 -0.0130 0.1228 1.0000 9.250 1.0756 0.02091 0.01305 -0.0110 0.1013 1.0000 9.500 1.0861 0.02202 0.01405 -0.0087 0.0797 1.0000 9.750 1.0970 0.02304 0.01500 -0.0065 0.0668 1.0000 10.000 1.1024 0.02422 0.01612 -0.0035 0.0599 1.0000 10.250 1.1100 0.02537 0.01734 -0.0010 0.0552 1.0000 10.500 1.1152 0.02675 0.01873 0.0014 0.0515 1.0000 10.750 1.1200 0.02832 0.02035 0.0037 0.0486 1.0000 11.000 1.1284 0.02970 0.02182 0.0055 0.0459 1.0000 11.250 1.1352 0.03128 0.02343 0.0071 0.0439 1.0000 11.500 1.1403 0.03329 0.02540 0.0090 0.0420 1.0000 11.750 1.1505 0.03490 0.02712 0.0103 0.0405 1.0000 12.000 1.1606 0.03646 0.02882 0.0116 0.0389 1.0000 12.250 1.1702 0.03809 0.03053 0.0127 0.0373 1.0000 12.500 1.1808 0.03979 0.03223 0.0137 0.0359 1.0000 12.750 1.2007 0.04211 0.03450 0.0149 0.0344 1.0000 13.000 1.2074 0.04402 0.03664 0.0160 0.0339 1.0000 13.250 1.2132 0.04618 0.03901 0.0171 0.0332 1.0000 13.500 1.2171 0.04853 0.04159 0.0181 0.0325 1.0000 13.750 1.2194 0.05103 0.04429 0.0189 0.0317 1.0000 14.000 1.2210 0.05359 0.04701 0.0195 0.0310 1.0000 14.250 1.2223 0.05621 0.04976 0.0199 0.0303 1.0000 14.500 1.2218 0.05911 0.05279 0.0202 0.0297 1.0000 14.750 1.2209 0.06226 0.05608 0.0204 0.0293 1.0000 15.000 1.2172 0.06587 0.05984 0.0204 0.0290 1.0000 15.250 1.2097 0.07004 0.06419 0.0201 0.0288 1.0000 15.500 1.1975 0.07472 0.06908 0.0193 0.0287 1.0000 15.750 1.1818 0.07983 0.07442 0.0179 0.0286 1.0000 16.000 1.1635 0.08539 0.08020 0.0158 0.0286 1.0000 16.250 1.1423 0.09164 0.08669 0.0127 0.0287 1.0000 16.500 1.1160 0.09931 0.09463 0.0083 0.0290 1.0000 16.750 1.0261 0.12137 0.11736 -0.0071 0.0308 1.0000 17.000 0.9326 0.15026 0.14654 -0.0253 0.0336 1.0000 17.250 0.9105 0.16176 0.15804 -0.0309 0.0344 1.0000