GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 100,000 Max Cl/Cd: 58.54 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe358-il-100000.txt Download as CSV file: xf-goe358-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 358 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3083 0.10209 0.09701 -0.0308 1.0000 0.1328
-8.000 -0.3393 0.10284 0.09794 -0.0306 1.0000 0.1363
-7.750 -0.3762 0.10374 0.09904 -0.0312 1.0000 0.1371
-7.500 -0.3243 0.09594 0.09110 -0.0271 1.0000 0.1413
-7.250 -0.3241 0.09423 0.08943 -0.0248 1.0000 0.1462
-7.000 -0.3457 0.09383 0.08916 -0.0222 1.0000 0.1501
-6.750 -0.3807 0.09363 0.08918 -0.0300 1.0000 0.1529
-6.500 -0.3611 0.08955 0.08506 -0.0200 1.0000 0.1558
-6.250 -0.3574 0.08766 0.08321 -0.0172 1.0000 0.1597
-6.000 -0.3732 0.08664 0.08230 -0.0227 1.0000 0.1676
-5.750 -0.3748 0.08338 0.07909 -0.0227 1.0000 0.1699
-5.500 -0.3713 0.08141 0.07716 -0.0178 1.0000 0.1722
-5.250 -0.2996 0.04896 0.04389 -0.0762 1.0000 0.1225
-5.000 -0.2907 0.04855 0.04363 -0.0724 1.0000 0.1237
-4.750 -0.2055 0.03382 0.02758 -0.0976 1.0000 0.1171
-4.500 -0.1623 0.03015 0.02312 -0.1038 1.0000 0.1198
-4.250 -0.1276 0.02826 0.02060 -0.1068 1.0000 0.1217
-4.000 -0.0880 0.02651 0.01870 -0.1102 0.9976 0.1253
-3.750 -0.0392 0.02547 0.01747 -0.1148 0.9925 0.1309
-3.500 0.0097 0.02445 0.01608 -0.1191 0.9863 0.1354
-3.250 0.0582 0.02350 0.01513 -0.1234 0.9799 0.1429
-3.000 0.1112 0.02273 0.01418 -0.1281 0.9718 0.1520
-2.750 0.1590 0.02186 0.01344 -0.1319 0.9617 0.1643
-2.500 0.2098 0.02101 0.01279 -0.1363 0.9535 0.1912
-2.250 0.2546 0.02084 0.01316 -0.1391 0.9436 0.2855
-2.000 0.2897 0.02170 0.01401 -0.1396 0.9313 0.3407
-1.750 0.3272 0.02222 0.01463 -0.1406 0.9213 0.3672
-1.500 0.3694 0.02232 0.01468 -0.1425 0.9126 0.3920
-1.250 0.4038 0.02240 0.01485 -0.1430 0.9015 0.4114
-1.000 0.4481 0.02219 0.01467 -0.1451 0.8951 0.4358
-0.750 0.4799 0.02201 0.01449 -0.1451 0.8827 0.4563
-0.500 0.5152 0.02158 0.01407 -0.1457 0.8719 0.4723
-0.250 0.5566 0.02088 0.01331 -0.1474 0.8634 0.4857
0.000 0.5881 0.02035 0.01280 -0.1474 0.8495 0.4953
0.250 0.6209 0.01985 0.01225 -0.1475 0.8355 0.5068
0.500 0.6540 0.01940 0.01173 -0.1478 0.8207 0.5186
0.750 0.6850 0.01894 0.01126 -0.1475 0.8049 0.5272
1.000 0.7170 0.01859 0.01079 -0.1476 0.7880 0.5347
1.250 0.7471 0.01827 0.01043 -0.1473 0.7701 0.5416
1.500 0.7778 0.01810 0.01011 -0.1471 0.7513 0.5497
1.750 0.8052 0.01801 0.00996 -0.1465 0.7303 0.5561
2.000 0.8329 0.01804 0.00989 -0.1460 0.7086 0.5637
2.250 0.8601 0.01806 0.00983 -0.1453 0.6880 0.5715
2.500 0.8881 0.01818 0.00982 -0.1449 0.6687 0.5806
2.750 0.9151 0.01829 0.00989 -0.1444 0.6501 0.5888
3.000 0.9421 0.01849 0.01002 -0.1440 0.6322 0.5984
3.250 0.9689 0.01866 0.01015 -0.1435 0.6161 0.6095
3.500 0.9958 0.01883 0.01027 -0.1430 0.6012 0.6220
3.750 1.0223 0.01900 0.01045 -0.1425 0.5867 0.6362
4.000 1.0482 0.01920 0.01071 -0.1420 0.5729 0.6529
4.250 1.0741 0.01943 0.01104 -0.1415 0.5611 0.6766
4.500 1.1000 0.01950 0.01130 -0.1409 0.5517 0.7212
4.750 1.1242 0.01955 0.01165 -0.1400 0.5416 1.0000
5.000 1.1524 0.02010 0.01213 -0.1401 0.5325 1.0000
5.250 1.1802 0.02060 0.01258 -0.1400 0.5236 1.0000
5.500 1.2062 0.02117 0.01318 -0.1397 0.5145 1.0000
5.750 1.2339 0.02160 0.01350 -0.1394 0.5052 1.0000
6.000 1.2575 0.02207 0.01408 -0.1385 0.4936 1.0000
6.250 1.2822 0.02249 0.01450 -0.1377 0.4820 1.0000
6.500 1.3076 0.02283 0.01478 -0.1370 0.4702 1.0000
6.750 1.3315 0.02318 0.01518 -0.1360 0.4578 1.0000
7.000 1.3539 0.02354 0.01563 -0.1348 0.4445 1.0000
7.250 1.3764 0.02388 0.01604 -0.1336 0.4311 1.0000
7.500 1.3986 0.02418 0.01638 -0.1323 0.4169 1.0000
7.750 1.4197 0.02445 0.01673 -0.1309 0.4015 1.0000
8.000 1.4390 0.02468 0.01703 -0.1291 0.3838 1.0000
8.250 1.4564 0.02488 0.01729 -0.1270 0.3634 1.0000
8.500 1.4708 0.02514 0.01761 -0.1244 0.3393 1.0000
8.750 1.4809 0.02548 0.01806 -0.1212 0.3059 1.0000
9.000 1.4838 0.02620 0.01870 -0.1171 0.2415 1.0000
9.250 1.4743 0.02841 0.02019 -0.1118 0.1808 1.0000
9.500 1.4654 0.03089 0.02238 -0.1067 0.1550 1.0000
9.750 1.4609 0.03309 0.02446 -0.1024 0.1381 1.0000
10.000 1.4609 0.03508 0.02642 -0.0988 0.1249 1.0000
10.250 1.4625 0.03704 0.02835 -0.0957 0.1147 1.0000
10.500 1.4646 0.03906 0.03026 -0.0929 0.1067 1.0000
10.750 1.4704 0.04090 0.03221 -0.0904 0.0989 1.0000
11.000 1.4775 0.04298 0.03415 -0.0882 0.0927 1.0000
11.250 1.4867 0.04489 0.03619 -0.0862 0.0871 1.0000
11.500 1.5045 0.04703 0.03809 -0.0849 0.0814 1.0000
11.750 1.5130 0.04910 0.04043 -0.0829 0.0775 1.0000
12.000 1.5282 0.05119 0.04258 -0.0815 0.0737 1.0000
12.250 1.5574 0.05399 0.04530 -0.0813 0.0695 1.0000
12.500 1.5593 0.05645 0.04809 -0.0790 0.0674 1.0000
12.750 1.5647 0.05912 0.05099 -0.0771 0.0652 1.0000
13.000 1.5716 0.06197 0.05403 -0.0755 0.0634 1.0000
13.250 1.5794 0.06492 0.05711 -0.0741 0.0617 1.0000
13.500 1.5969 0.06965 0.06191 -0.0738 0.0595 1.0000
13.750 1.5797 0.07294 0.06555 -0.0711 0.0591 1.0000
14.000 1.5615 0.07675 0.06969 -0.0692 0.0587 1.0000
14.250 1.5427 0.08106 0.07432 -0.0680 0.0584 1.0000
14.500 1.5221 0.08589 0.07945 -0.0676 0.0582 1.0000
14.750 1.5003 0.09123 0.08510 -0.0679 0.0581 1.0000
15.000 1.4768 0.09715 0.09129 -0.0691 0.0581 1.0000
15.250 1.4522 0.10362 0.09803 -0.0710 0.0582 1.0000
15.500 1.4268 0.11071 0.10536 -0.0739 0.0585 1.0000
15.750 1.4007 0.11847 0.11334 -0.0778 0.0588 1.0000
16.000 1.3747 0.12698 0.12205 -0.0825 0.0591 1.0000
16.250 1.3502 0.13606 0.13127 -0.0879 0.0595 1.0000
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