XFOIL Version 6.96 Calculated polar for: GOE 776 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2029 0.08721 0.08194 -0.0458 1.0000 0.1048 -19.500 -1.2042 0.08398 0.07862 -0.0468 1.0000 0.1067 -19.250 -1.2032 0.08112 0.07569 -0.0476 1.0000 0.1085 -19.000 -1.2047 0.07809 0.07268 -0.0483 1.0000 0.1106 -18.750 -1.2047 0.07516 0.06973 -0.0490 1.0000 0.1126 -18.500 -1.2043 0.07226 0.06676 -0.0497 1.0000 0.1145 -18.250 -1.2013 0.06965 0.06407 -0.0503 1.0000 0.1165 -18.000 -1.2008 0.06692 0.06132 -0.0508 1.0000 0.1185 -17.750 -1.2008 0.06416 0.05856 -0.0512 1.0000 0.1206 -17.500 -1.1998 0.06145 0.05581 -0.0516 1.0000 0.1227 -17.250 -1.1954 0.05913 0.05344 -0.0520 1.0000 0.1249 -17.000 -1.1904 0.05685 0.05107 -0.0523 1.0000 0.1268 -16.750 -1.1899 0.05435 0.04859 -0.0523 1.0000 0.1292 -16.500 -1.1883 0.05187 0.04609 -0.0524 1.0000 0.1314 -16.250 -1.1835 0.04973 0.04392 -0.0525 1.0000 0.1338 -16.000 -1.1766 0.04781 0.04194 -0.0525 1.0000 0.1361 -15.750 -1.1719 0.04579 0.03988 -0.0523 1.0000 0.1385 -15.500 -1.1697 0.04358 0.03768 -0.0520 1.0000 0.1410 -15.250 -1.1648 0.04162 0.03570 -0.0518 1.0000 0.1436 -15.000 -1.1562 0.04003 0.03406 -0.0514 1.0000 0.1463 -14.750 -1.1485 0.03842 0.03240 -0.0510 1.0000 0.1489 -14.500 -1.1456 0.03652 0.03053 -0.0503 1.0000 0.1518 -14.250 -1.1398 0.03490 0.02890 -0.0495 1.0000 0.1548 -14.000 -1.1310 0.03358 0.02753 -0.0487 1.0000 0.1579 -13.750 -1.1231 0.03230 0.02623 -0.0477 1.0000 0.1608 -13.500 -1.1214 0.03076 0.02471 -0.0461 1.0000 0.1640 -13.250 -1.1172 0.02957 0.02352 -0.0443 1.0000 0.1673 -13.000 -1.1116 0.02861 0.02253 -0.0424 1.0000 0.1705 -12.750 -1.1098 0.02763 0.02153 -0.0398 1.0000 0.1736 -12.500 -1.1137 0.02659 0.02051 -0.0364 1.0000 0.1769 -12.250 -1.1177 0.02578 0.01970 -0.0326 1.0000 0.1801 -12.000 -1.1217 0.02515 0.01905 -0.0286 1.0000 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0.4513 0.6191 2.500 0.2268 0.01101 0.00448 0.0075 0.4425 0.6299 2.750 0.2509 0.01110 0.00455 0.0083 0.4344 0.6406 3.000 0.2751 0.01111 0.00462 0.0092 0.4261 0.6514 3.250 0.2979 0.01123 0.00470 0.0102 0.4178 0.6625 3.500 0.3224 0.01126 0.00479 0.0109 0.4105 0.6732 3.750 0.3460 0.01133 0.00487 0.0118 0.4026 0.6849 4.000 0.3680 0.01146 0.00499 0.0130 0.3946 0.6959 4.250 0.3925 0.01149 0.00508 0.0137 0.3877 0.7078 4.500 0.4152 0.01159 0.00519 0.0147 0.3801 0.7192 4.750 0.4369 0.01172 0.00533 0.0160 0.3727 0.7317 5.000 0.4604 0.01177 0.00545 0.0169 0.3657 0.7436 5.250 0.4802 0.01190 0.00557 0.0185 0.3582 0.7566 5.500 0.5004 0.01201 0.00573 0.0200 0.3514 0.7690 5.750 0.5216 0.01212 0.00587 0.0213 0.3445 0.7824 6.000 0.5411 0.01229 0.00607 0.0229 0.3374 0.7952 6.500 0.5851 0.01263 0.00650 0.0251 0.3243 0.8214 6.750 0.6046 0.01290 0.00674 0.0265 0.3174 0.8347 7.000 0.6268 0.01309 0.00700 0.0276 0.3112 0.8478 7.250 0.6479 0.01332 0.00726 0.0288 0.3047 0.8602 7.500 0.6659 0.01366 0.00759 0.0304 0.2980 0.8737 7.750 0.6878 0.01389 0.00788 0.0315 0.2922 0.8853 8.000 0.7067 0.01418 0.00819 0.0330 0.2857 0.8984 8.250 0.7235 0.01462 0.00861 0.0349 0.2793 0.9098 8.500 0.7437 0.01487 0.00891 0.0362 0.2739 0.9220 8.750 0.7621 0.01528 0.00934 0.0377 0.2677 0.9328 9.000 0.7783 0.01579 0.00981 0.0395 0.2616 0.9442 9.250 0.8009 0.01616 0.01023 0.0402 0.2559 0.9539 9.500 0.8230 0.01670 0.01074 0.0407 0.2497 0.9624 9.750 0.8502 0.01731 0.01132 0.0400 0.2435 0.9686 10.000 0.8758 0.01781 0.01184 0.0397 0.2374 0.9761 10.250 0.9074 0.01859 0.01255 0.0377 0.2305 0.9787 10.500 0.9424 0.01916 0.01314 0.0354 0.2244 0.9810 10.750 0.9730 0.01990 0.01385 0.0336 0.2179 0.9842 11.000 1.0007 0.02068 0.01462 0.0323 0.2120 0.9885 11.250 1.0303 0.02137 0.01531 0.0308 0.2061 0.9915 11.500 1.0572 0.02238 0.01626 0.0290 0.1999 0.9938 11.750 1.0885 0.02307 0.01699 0.0270 0.1946 0.9963 12.000 1.1154 0.02405 0.01794 0.0254 0.1892 0.9989 12.250 1.1204 0.02500 0.01887 0.0274 0.1851 1.0000 12.500 1.1179 0.02554 0.01946 0.0314 0.1822 1.0000 12.750 1.1155 0.02626 0.02019 0.0350 0.1789 1.0000 13.000 1.1131 0.02720 0.02111 0.0383 0.1757 1.0000 13.250 1.1101 0.02840 0.02229 0.0413 0.1723 1.0000 13.500 1.1178 0.02923 0.02316 0.0432 0.1693 1.0000 13.750 1.1233 0.03034 0.02429 0.0449 0.1659 1.0000 14.000 1.1270 0.03174 0.02568 0.0464 0.1627 1.0000 14.250 1.1312 0.03325 0.02718 0.0476 0.1594 1.0000 14.500 1.1415 0.03447 0.02845 0.0483 0.1565 1.0000 14.750 1.1490 0.03595 0.02995 0.0490 0.1534 1.0000 15.000 1.1533 0.03775 0.03175 0.0497 0.1505 1.0000 15.250 1.1575 0.03961 0.03361 0.0503 0.1477 1.0000 15.500 1.1675 0.04109 0.03516 0.0506 0.1450 1.0000 15.750 1.1736 0.04295 0.03705 0.0508 0.1423 1.0000 16.000 1.1774 0.04502 0.03912 0.0511 0.1397 1.0000 16.250 1.1789 0.04732 0.04141 0.0513 0.1371 1.0000 16.500 1.1871 0.04912 0.04329 0.0513 0.1349 1.0000 16.750 1.1925 0.05122 0.04543 0.0512 0.1324 1.0000 17.000 1.1951 0.05359 0.04783 0.0511 0.1301 1.0000 17.250 1.1954 0.05617 0.05039 0.0510 0.1278 1.0000 17.500 1.1993 0.05849 0.05278 0.0508 0.1257 1.0000 17.750 1.2041 0.06078 0.05513 0.0504 0.1235 1.0000 18.000 1.2057 0.06342 0.05781 0.0500 0.1213 1.0000 18.250 1.2061 0.06617 0.06056 0.0496 0.1192 1.0000 18.500 1.2057 0.06898 0.06338 0.0492 0.1170 1.0000 18.750 1.2089 0.07156 0.06604 0.0486 0.1152 1.0000 19.000 1.2096 0.07444 0.06899 0.0479 0.1131 1.0000 19.250 1.2100 0.07733 0.07190 0.0472 0.1111 1.0000