XFOIL Version 6.96 Calculated polar for: GOE 528 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.0623 0.08448 0.08165 -0.0986 0.8881 0.0165 -10.000 -0.0436 0.08240 0.07947 -0.1014 0.8696 0.0169 -9.750 -0.0361 0.07947 0.07646 -0.1033 0.8537 0.0172 -9.500 -0.0296 0.07693 0.07386 -0.1045 0.8392 0.0177 -9.000 -0.0548 0.06583 0.06267 -0.1091 0.8136 0.0194 -8.750 -0.0517 0.06367 0.06049 -0.1096 0.8024 0.0196 -8.250 -0.1838 0.02614 0.02184 -0.1315 0.7774 0.0230 -8.000 -0.1651 0.02486 0.02043 -0.1311 0.7698 0.0233 -7.750 -0.1431 0.02421 0.01968 -0.1307 0.7625 0.0235 -7.500 -0.1212 0.02340 0.01875 -0.1302 0.7544 0.0239 -7.250 -0.0999 0.02242 0.01759 -0.1297 0.7468 0.0242 -7.000 -0.0795 0.02097 0.01589 -0.1292 0.7390 0.0247 -6.750 -0.0587 0.01960 0.01423 -0.1285 0.7317 0.0252 -6.500 -0.0368 0.01826 0.01261 -0.1278 0.7237 0.0259 -6.250 -0.0140 0.01725 0.01129 -0.1271 0.7157 0.0265 -6.000 0.0101 0.01644 0.01024 -0.1265 0.7072 0.0269 -5.750 0.0342 0.01570 0.00927 -0.1259 0.6990 0.0272 -5.500 0.0586 0.01487 0.00833 -0.1254 0.6903 0.0276 -5.250 0.0834 0.01438 0.00772 -0.1248 0.6811 0.0280 -5.000 0.1090 0.01396 0.00722 -0.1243 0.6713 0.0284 -4.750 0.1346 0.01363 0.00678 -0.1238 0.6620 0.0289 -4.500 0.1602 0.01330 0.00635 -0.1233 0.6514 0.0294 -4.250 0.1858 0.01295 0.00589 -0.1227 0.6409 0.0299 -4.000 0.2113 0.01262 0.00545 -0.1221 0.6303 0.0304 -3.750 0.2369 0.01231 0.00504 -0.1216 0.6192 0.0307 -3.500 0.2626 0.01205 0.00469 -0.1210 0.6084 0.0311 -3.250 0.2881 0.01184 0.00437 -0.1204 0.5978 0.0315 -3.000 0.3139 0.01165 0.00410 -0.1199 0.5875 0.0319 -2.750 0.3393 0.01140 0.00378 -0.1193 0.5779 0.0323 -2.500 0.3646 0.01119 0.00353 -0.1188 0.5685 0.0331 -2.250 0.3907 0.01105 0.00335 -0.1183 0.5602 0.0339 -2.000 0.4164 0.01095 0.00320 -0.1178 0.5522 0.0347 -1.750 0.4426 0.01085 0.00305 -0.1173 0.5448 0.0353 -1.500 0.4687 0.01077 0.00292 -0.1169 0.5377 0.0361 -1.250 0.4948 0.01071 0.00281 -0.1164 0.5313 0.0369 -1.000 0.5212 0.01065 0.00272 -0.1160 0.5249 0.0376 -0.750 0.5471 0.01059 0.00263 -0.1155 0.5189 0.0391 -0.500 0.5735 0.01055 0.00257 -0.1151 0.5134 0.0410 -0.250 0.6000 0.01053 0.00253 -0.1148 0.5076 0.0438 0.000 0.6258 0.01052 0.00251 -0.1143 0.5022 0.0487 0.250 0.6521 0.01048 0.00251 -0.1139 0.4971 0.0618 0.500 0.6783 0.01041 0.00252 -0.1135 0.4918 0.0910 0.750 0.7037 0.01034 0.00255 -0.1131 0.4867 0.1372 1.000 0.7289 0.01022 0.00262 -0.1126 0.4820 0.2195 1.250 0.7541 0.01004 0.00271 -0.1122 0.4767 0.3219 1.500 0.7778 0.00982 0.00283 -0.1115 0.4714 0.4601 1.750 0.8319 0.00887 0.00306 -0.1173 0.4654 1.0000 2.000 0.8572 0.00897 0.00312 -0.1167 0.4600 1.0000 2.250 0.8817 0.00910 0.00319 -0.1160 0.4543 1.0000 2.500 0.9062 0.00924 0.00327 -0.1153 0.4490 1.0000 2.750 0.9313 0.00935 0.00335 -0.1147 0.4432 1.0000 3.000 0.9555 0.00950 0.00344 -0.1140 0.4370 1.0000 3.250 0.9800 0.00964 0.00354 -0.1133 0.4309 1.0000 3.500 1.0043 0.00978 0.00364 -0.1126 0.4237 1.0000 3.750 1.0279 0.00995 0.00376 -0.1118 0.4172 1.0000 4.000 1.0524 0.01009 0.00388 -0.1111 0.4105 1.0000 4.250 1.0759 0.01027 0.00402 -0.1103 0.4042 1.0000 4.500 1.0998 0.01043 0.00416 -0.1096 0.3977 1.0000 4.750 1.1232 0.01060 0.00431 -0.1088 0.3909 1.0000 5.000 1.1462 0.01080 0.00448 -0.1079 0.3851 1.0000 5.250 1.1698 0.01097 0.00464 -0.1071 0.3788 1.0000 5.500 1.1920 0.01118 0.00483 -0.1062 0.3725 1.0000 5.750 1.2148 0.01138 0.00502 -0.1053 0.3662 1.0000 6.000 1.2360 0.01162 0.00523 -0.1041 0.3578 1.0000 6.250 1.2574 0.01185 0.00545 -0.1030 0.3496 1.0000 6.500 1.2770 0.01214 0.00570 -0.1016 0.3406 1.0000 6.750 1.2976 0.01238 0.00594 -0.1004 0.3331 1.0000 7.250 1.3337 0.01294 0.00647 -0.0970 0.3169 1.0000 7.500 1.3501 0.01328 0.00679 -0.0951 0.3093 1.0000 7.750 1.3684 0.01358 0.00709 -0.0935 0.3012 1.0000 8.000 1.3840 0.01397 0.00745 -0.0915 0.2934 1.0000 8.250 1.4013 0.01432 0.00781 -0.0899 0.2844 1.0000 8.500 1.4168 0.01475 0.00822 -0.0880 0.2773 1.0000 8.750 1.4337 0.01513 0.00862 -0.0864 0.2698 1.0000 9.000 1.4478 0.01564 0.00910 -0.0844 0.2616 1.0000 9.250 1.4633 0.01610 0.00958 -0.0827 0.2538 1.0000 9.500 1.4769 0.01666 0.01014 -0.0808 0.2472 1.0000 9.750 1.4921 0.01718 0.01068 -0.0792 0.2403 1.0000 10.000 1.5039 0.01786 0.01136 -0.0772 0.2328 1.0000 10.250 1.5178 0.01848 0.01201 -0.0756 0.2255 1.0000 10.750 1.5420 0.01998 0.01354 -0.0721 0.2122 1.0000 11.000 1.5519 0.02090 0.01446 -0.0703 0.2053 1.0000 11.250 1.5622 0.02184 0.01542 -0.0686 0.1963 1.0000 11.500 1.5696 0.02300 0.01657 -0.0667 0.1871 1.0000 11.750 1.5741 0.02441 0.01794 -0.0648 0.1751 1.0000 12.000 1.5808 0.02572 0.01926 -0.0631 0.1649 1.0000 12.250 1.5848 0.02729 0.02081 -0.0614 0.1532 1.0000 12.500 1.5853 0.02918 0.02267 -0.0595 0.1386 1.0000 12.750 1.5725 0.03225 0.02557 -0.0571 0.1089 1.0000 13.250 1.5577 0.03796 0.03121 -0.0538 0.0834 1.0000 13.500 1.5545 0.04064 0.03392 -0.0526 0.0779 1.0000 13.750 1.5574 0.04282 0.03617 -0.0519 0.0751 1.0000 14.000 1.5563 0.04548 0.03889 -0.0512 0.0712 1.0000 14.250 1.5532 0.04844 0.04190 -0.0505 0.0678 1.0000 14.500 1.5547 0.05097 0.04452 -0.0501 0.0656 1.0000 14.750 1.5557 0.05363 0.04725 -0.0498 0.0628 1.0000 15.000 1.5539 0.05666 0.05035 -0.0496 0.0599 1.0000 15.250 1.5502 0.06001 0.05376 -0.0495 0.0575 1.0000 15.500 1.5501 0.06295 0.05678 -0.0495 0.0553 1.0000 15.750 1.5487 0.06610 0.06002 -0.0496 0.0529 1.0000 16.000 1.5446 0.06966 0.06363 -0.0498 0.0501 1.0000 16.250 1.5401 0.07333 0.06737 -0.0501 0.0478 1.0000 16.500 1.5356 0.07704 0.07115 -0.0505 0.0442 1.0000 16.750 1.5300 0.08095 0.07512 -0.0510 0.0419 1.0000 17.000 1.5252 0.08483 0.07906 -0.0516 0.0388 1.0000 17.250 1.5189 0.08900 0.08330 -0.0524 0.0361 1.0000 17.500 1.5116 0.09334 0.08770 -0.0533 0.0332 1.0000 17.750 1.5037 0.09786 0.09228 -0.0544 0.0301 1.0000 18.000 1.4962 0.10238 0.09686 -0.0555 0.0271 1.0000 18.250 1.4877 0.10713 0.10167 -0.0569 0.0243 1.0000 18.500 1.4791 0.11195 0.10655 -0.0584 0.0218 1.0000