XFOIL Version 6.96 Calculated polar for: GOE 476 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -1.0948 0.02856 0.02498 -0.1244 0.9895 0.0332 -15.750 -1.0852 0.02698 0.02330 -0.1241 0.9844 0.0334 -15.500 -1.0675 0.02564 0.02188 -0.1244 0.9809 0.0336 -15.250 -1.0535 0.02455 0.02071 -0.1235 0.9745 0.0338 -15.000 -1.0317 0.02355 0.01965 -0.1237 0.9702 0.0341 -14.750 -1.0061 0.02265 0.01867 -0.1245 0.9665 0.0344 -14.500 -0.9823 0.02188 0.01783 -0.1247 0.9600 0.0348 -14.250 -0.9503 0.02103 0.01690 -0.1266 0.9555 0.0351 -14.000 -0.9166 0.02022 0.01600 -0.1287 0.9504 0.0354 -13.750 -0.8846 0.01946 0.01515 -0.1303 0.9424 0.0357 -13.500 -0.8510 0.01875 0.01434 -0.1322 0.9334 0.0360 -13.250 -0.8197 0.01811 0.01358 -0.1335 0.9203 0.0363 -13.000 -0.7933 0.01760 0.01294 -0.1337 0.9032 0.0366 -12.750 -0.7709 0.01716 0.01237 -0.1329 0.8844 0.0367 -12.500 -0.7515 0.01673 0.01180 -0.1316 0.8657 0.0370 -12.250 -0.7336 0.01628 0.01123 -0.1299 0.8480 0.0374 -12.000 -0.7141 0.01590 0.01077 -0.1284 0.8334 0.0377 -11.750 -0.6934 0.01559 0.01038 -0.1271 0.8207 0.0381 -11.500 -0.6725 0.01529 0.00999 -0.1258 0.8094 0.0384 -11.250 -0.6504 0.01499 0.00963 -0.1248 0.7993 0.0388 -11.000 -0.6286 0.01471 0.00926 -0.1236 0.7894 0.0391 -10.750 -0.6060 0.01442 0.00890 -0.1226 0.7798 0.0395 -10.500 -0.5837 0.01416 0.00855 -0.1215 0.7702 0.0398 -10.250 -0.5606 0.01388 0.00820 -0.1205 0.7603 0.0402 -10.000 -0.5378 0.01364 0.00787 -0.1194 0.7499 0.0405 -9.750 -0.5144 0.01339 0.00754 -0.1185 0.7391 0.0408 -9.500 -0.4910 0.01317 0.00724 -0.1175 0.7286 0.0411 -9.250 -0.4673 0.01296 0.00695 -0.1166 0.7180 0.0413 -9.000 -0.4441 0.01267 0.00659 -0.1156 0.7087 0.0418 -8.750 -0.4206 0.01244 0.00630 -0.1146 0.6983 0.0424 -8.500 -0.3962 0.01224 0.00605 -0.1138 0.6890 0.0429 -8.250 -0.3720 0.01207 0.00582 -0.1130 0.6792 0.0434 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0.0563 -3.250 0.1447 0.00946 0.00258 -0.1012 0.5780 0.0572 -3.000 0.1714 0.00939 0.00250 -0.1007 0.5743 0.0580 -2.750 0.1974 0.00929 0.00240 -0.1002 0.5702 0.0594 -2.500 0.2233 0.00923 0.00233 -0.0996 0.5661 0.0610 -2.250 0.2498 0.00916 0.00226 -0.0991 0.5628 0.0626 -2.000 0.2767 0.00910 0.00220 -0.0987 0.5595 0.0642 -1.750 0.3031 0.00903 0.00214 -0.0982 0.5556 0.0666 -1.500 0.3291 0.00898 0.00209 -0.0977 0.5515 0.0691 -1.250 0.3549 0.00895 0.00205 -0.0970 0.5474 0.0715 -1.000 0.3813 0.00889 0.00201 -0.0966 0.5435 0.0751 -0.750 0.4075 0.00884 0.00197 -0.0961 0.5385 0.0792 -0.500 0.4326 0.00881 0.00194 -0.0953 0.5314 0.0852 -0.250 0.4580 0.00877 0.00193 -0.0947 0.5259 0.0938 0.000 0.4837 0.00872 0.00193 -0.0941 0.5194 0.1051 0.250 0.5082 0.00873 0.00194 -0.0932 0.5118 0.1157 0.500 0.5341 0.00873 0.00195 -0.0927 0.5059 0.1236 0.750 0.5592 0.00874 0.00198 -0.0920 0.4986 0.1316 1.000 0.5840 0.00879 0.00200 -0.0912 0.4914 0.1361 1.250 0.6091 0.00880 0.00203 -0.0905 0.4842 0.1418 1.500 0.6330 0.00886 0.00206 -0.0895 0.4764 0.1466 1.750 0.6581 0.00890 0.00210 -0.0888 0.4698 0.1500 2.000 0.6823 0.00895 0.00214 -0.0880 0.4631 0.1550 2.250 0.7063 0.00900 0.00219 -0.0871 0.4577 0.1602 2.500 0.7310 0.00903 0.00224 -0.0863 0.4522 0.1649 2.750 0.7543 0.00909 0.00230 -0.0853 0.4456 0.1733 3.000 0.7774 0.00915 0.00237 -0.0842 0.4397 0.1842 3.250 0.8009 0.00917 0.00245 -0.0832 0.4339 0.2001 3.500 0.8230 0.00923 0.00253 -0.0820 0.4275 0.2200 3.750 0.8448 0.00926 0.00263 -0.0807 0.4223 0.2508 4.000 0.8661 0.00922 0.00271 -0.0793 0.4183 0.2999 4.250 0.8796 0.00891 0.00285 -0.0764 0.4134 0.4915 4.750 1.0183 0.00874 0.00371 -0.0951 0.3824 0.9833 5.000 1.0497 0.00902 0.00391 -0.0959 0.3696 0.9887 5.250 1.0793 0.00932 0.00413 -0.0965 0.3546 0.9933 5.500 1.1216 0.00965 0.00436 -0.0999 0.3362 0.9977 5.750 1.1569 0.01015 0.00468 -0.1019 0.3043 1.0000 6.000 1.1548 0.01078 0.00509 -0.0961 0.2632 1.0000 6.250 1.1544 0.01120 0.00540 -0.0905 0.2426 1.0000 6.500 1.1600 0.01156 0.00568 -0.0861 0.2282 1.0000 6.750 1.1700 0.01187 0.00595 -0.0827 0.2184 1.0000 7.000 1.1799 0.01223 0.00626 -0.0793 0.2090 1.0000 7.250 1.1947 0.01249 0.00651 -0.0769 0.2044 1.0000 7.500 1.2080 0.01281 0.00681 -0.0743 0.1978 1.0000 7.750 1.2212 0.01318 0.00715 -0.0717 0.1917 1.0000 8.000 1.2374 0.01347 0.00745 -0.0697 0.1883 1.0000 8.250 1.2534 0.01380 0.00777 -0.0678 0.1841 1.0000 8.500 1.2678 0.01420 0.00816 -0.0656 0.1791 1.0000 8.750 1.2826 0.01463 0.00858 -0.0636 0.1741 1.0000 9.000 1.2985 0.01502 0.00898 -0.0618 0.1698 1.0000 9.250 1.3125 0.01553 0.00947 -0.0599 0.1638 1.0000 9.500 1.3263 0.01607 0.01000 -0.0579 0.1582 1.0000 9.750 1.3398 0.01666 0.01057 -0.0561 0.1513 1.0000 10.000 1.3518 0.01736 0.01124 -0.0541 0.1441 1.0000 10.250 1.3623 0.01817 0.01201 -0.0520 0.1355 1.0000 10.500 1.3742 0.01895 0.01278 -0.0503 0.1294 1.0000 10.750 1.3830 0.01994 0.01373 -0.0482 0.1213 1.0000 11.000 1.3933 0.02090 0.01468 -0.0465 0.1141 1.0000 11.250 1.4020 0.02200 0.01576 -0.0447 0.1078 1.0000 11.500 1.4114 0.02309 0.01686 -0.0431 0.1017 1.0000 11.750 1.4186 0.02438 0.01813 -0.0414 0.0946 1.0000 12.000 1.4228 0.02594 0.01965 -0.0396 0.0846 1.0000 12.250 1.4237 0.02778 0.02144 -0.0377 0.0725 1.0000 12.500 1.4253 0.02966 0.02329 -0.0360 0.0645 1.0000 12.750 1.4311 0.03128 0.02492 -0.0347 0.0608 1.0000 13.000 1.4385 0.03280 0.02646 -0.0336 0.0588 1.0000 13.250 1.4445 0.03449 0.02817 -0.0325 0.0568 1.0000 13.500 1.4516 0.03611 0.02982 -0.0316 0.0551 1.0000 13.750 1.4596 0.03769 0.03145 -0.0307 0.0541 1.0000 14.000 1.4667 0.03938 0.03318 -0.0299 0.0533 1.0000 14.250 1.4736 0.04111 0.03494 -0.0291 0.0524 1.0000 14.500 1.4796 0.04295 0.03682 -0.0284 0.0516 1.0000 14.750 1.4845 0.04492 0.03883 -0.0276 0.0508 1.0000 15.000 1.4877 0.04708 0.04102 -0.0269 0.0491 1.0000 15.250 1.4941 0.04896 0.04296 -0.0264 0.0489 1.0000 15.500 1.5016 0.05073 0.04478 -0.0259 0.0484 1.0000 15.750 1.5069 0.05277 0.04687 -0.0254 0.0476 1.0000 16.000 1.5128 0.05475 0.04890 -0.0250 0.0472 1.0000 16.250 1.5168 0.05697 0.05117 -0.0246 0.0465 1.0000 16.500 1.5217 0.05908 0.05334 -0.0242 0.0462 1.0000 16.750 1.5238 0.06155 0.05585 -0.0239 0.0454 1.0000 17.000 1.5267 0.06392 0.05826 -0.0236 0.0446 1.0000 17.250 1.5275 0.06661 0.06099 -0.0235 0.0438 1.0000 17.500 1.5298 0.06911 0.06355 -0.0233 0.0432 1.0000 17.750 1.5331 0.07155 0.06605 -0.0233 0.0428 1.0000 18.000 1.5376 0.07383 0.06839 -0.0232 0.0424 1.0000 18.250 1.5395 0.07648 0.07111 -0.0233 0.0420 1.0000 18.500 1.5428 0.07896 0.07364 -0.0233 0.0414 1.0000 18.750 1.5437 0.08177 0.07652 -0.0235 0.0410 1.0000 19.000 1.5454 0.08445 0.07925 -0.0237 0.0401 1.0000 19.250 1.5448 0.08746 0.08231 -0.0239 0.0395 1.0000