GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Reynolds number: 200,000 Max Cl/Cd: 88.78 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe304-il-200000.txt Download as CSV file: xf-goe304-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 304 (FRIEDRICHSHAFEN G02) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2610 0.11104 0.10753 -0.0301 1.0000 0.0379
-8.750 -0.2713 0.11021 0.10678 -0.0271 1.0000 0.0382
-8.500 -0.2756 0.10880 0.10542 -0.0259 0.9992 0.0387
-8.250 -0.2555 0.10501 0.10162 -0.0314 0.9954 0.0398
-8.000 -0.2385 0.10230 0.09890 -0.0407 0.9879 0.0408
-7.750 -0.2194 0.09842 0.09501 -0.0500 0.9798 0.0412
-7.500 -0.1983 0.09375 0.09034 -0.0490 0.9781 0.0416
-7.250 -0.1750 0.08989 0.08647 -0.0526 0.9736 0.0423
-7.000 -0.1482 0.08600 0.08256 -0.0583 0.9691 0.0432
-6.750 -0.1242 0.08241 0.07896 -0.0638 0.9613 0.0443
-6.500 -0.0896 0.07824 0.07476 -0.0732 0.9574 0.0460
-6.250 -0.0446 0.07385 0.07023 -0.0923 0.9456 0.0472
-6.000 -0.0261 0.06992 0.06633 -0.0907 0.9433 0.0478
-5.750 -0.0058 0.06691 0.06332 -0.0918 0.9360 0.0486
-5.500 0.0219 0.06369 0.06008 -0.0961 0.9294 0.0498
-5.250 0.0511 0.06049 0.05682 -0.1011 0.9221 0.0514
-5.000 0.1112 0.05634 0.05231 -0.1183 0.9122 0.0543
-4.750 0.1239 0.05311 0.04915 -0.1167 0.9040 0.0548
-4.500 0.1431 0.05051 0.04655 -0.1167 0.8964 0.0556
-4.250 0.1655 0.04820 0.04420 -0.1178 0.8875 0.0569
-4.000 0.2224 0.04595 0.04143 -0.1278 0.8791 0.0627
-3.750 0.2381 0.04236 0.03791 -0.1275 0.8698 0.0634
-3.500 0.2588 0.04006 0.03561 -0.1275 0.8620 0.0644
-3.250 0.2815 0.03824 0.03374 -0.1279 0.8523 0.0661
-3.000 0.3122 0.03623 0.03157 -0.1297 0.8448 0.0698
-2.750 0.3467 0.03374 0.02876 -0.1325 0.8354 0.0742
-2.500 0.3708 0.03201 0.02699 -0.1327 0.8279 0.0762
-2.250 0.3976 0.03063 0.02551 -0.1332 0.8186 0.0806
-2.000 0.4293 0.02873 0.02332 -0.1346 0.8112 0.0872
-1.750 0.4541 0.02757 0.02214 -0.1346 0.8022 0.0920
-1.500 0.4855 0.02608 0.02034 -0.1355 0.7948 0.1006
-1.250 0.5109 0.02498 0.01921 -0.1355 0.7862 0.1058
-1.000 0.5402 0.02376 0.01777 -0.1359 0.7785 0.1164
-0.750 0.5684 0.02292 0.01675 -0.1361 0.7705 0.1302
-0.500 0.5959 0.02208 0.01578 -0.1362 0.7624 0.1460
-0.250 0.6223 0.02114 0.01478 -0.1362 0.7548 0.1633
0.000 0.6478 0.02028 0.01394 -0.1361 0.7464 0.1852
0.250 0.6897 0.01842 0.01109 -0.1353 0.7402 0.0963
0.500 0.7186 0.01708 0.00949 -0.1348 0.7316 0.0818
1.000 0.7744 0.01592 0.00806 -0.1340 0.7156 0.0811
1.250 0.8031 0.01549 0.00748 -0.1337 0.7085 0.0820
1.500 0.8293 0.01516 0.00714 -0.1331 0.6990 0.0830
1.750 0.8574 0.01485 0.00672 -0.1327 0.6907 0.0850
2.000 0.8827 0.01446 0.00644 -0.1319 0.6785 0.0908
2.250 0.9087 0.01426 0.00622 -0.1312 0.6666 0.0958
2.500 0.9358 0.01403 0.00596 -0.1308 0.6568 0.1031
2.750 0.9616 0.01393 0.00592 -0.1302 0.6462 0.1165
3.000 0.9884 0.01370 0.00589 -0.1299 0.6371 0.1930
3.250 1.0135 0.01243 0.00588 -0.1290 0.6270 1.0000
3.500 1.0391 0.01259 0.00594 -0.1284 0.6158 1.0000
3.750 1.0654 0.01274 0.00597 -0.1278 0.6054 1.0000
4.000 1.0905 0.01288 0.00607 -0.1271 0.5935 1.0000
4.250 1.1156 0.01305 0.00620 -0.1264 0.5816 1.0000
4.500 1.1409 0.01322 0.00630 -0.1258 0.5700 1.0000
4.750 1.1657 0.01339 0.00639 -0.1251 0.5575 1.0000
5.000 1.1899 0.01356 0.00657 -0.1242 0.5440 1.0000
5.250 1.2141 0.01376 0.00676 -0.1235 0.5308 1.0000
5.500 1.2381 0.01398 0.00694 -0.1227 0.5174 1.0000
5.750 1.2617 0.01422 0.00714 -0.1218 0.5032 1.0000
6.000 1.2846 0.01447 0.00736 -0.1208 0.4876 1.0000
6.250 1.3065 0.01476 0.00760 -0.1196 0.4697 1.0000
6.500 1.3278 0.01508 0.00788 -0.1184 0.4511 1.0000
6.750 1.3489 0.01546 0.00820 -0.1172 0.4331 1.0000
7.000 1.3690 0.01588 0.00857 -0.1158 0.4140 1.0000
7.250 1.3881 0.01635 0.00897 -0.1143 0.3943 1.0000
7.500 1.4066 0.01686 0.00942 -0.1127 0.3740 1.0000
7.750 1.4242 0.01740 0.00991 -0.1110 0.3528 1.0000
8.000 1.4404 0.01802 0.01046 -0.1091 0.3323 1.0000
8.250 1.4554 0.01871 0.01106 -0.1071 0.3134 1.0000
8.500 1.4696 0.01943 0.01170 -0.1049 0.2962 1.0000
8.750 1.4833 0.02018 0.01239 -0.1027 0.2806 1.0000
9.000 1.4953 0.02091 0.01311 -0.1003 0.2666 1.0000
9.250 1.5071 0.02169 0.01388 -0.0978 0.2537 1.0000
9.500 1.5182 0.02254 0.01472 -0.0954 0.2414 1.0000
9.750 1.5277 0.02350 0.01563 -0.0929 0.2294 1.0000
10.000 1.5355 0.02459 0.01664 -0.0902 0.2177 1.0000
10.250 1.5451 0.02557 0.01768 -0.0880 0.2054 1.0000
10.500 1.5536 0.02668 0.01882 -0.0857 0.1938 1.0000
10.750 1.5604 0.02796 0.02008 -0.0833 0.1837 1.0000
11.000 1.5673 0.02927 0.02137 -0.0811 0.1742 1.0000
11.250 1.5758 0.03053 0.02271 -0.0792 0.1653 1.0000
11.500 1.5809 0.03206 0.02418 -0.0771 0.1580 1.0000
11.750 1.5905 0.03332 0.02557 -0.0756 0.1508 1.0000
12.000 1.5962 0.03489 0.02712 -0.0738 0.1449 1.0000
12.250 1.6043 0.03634 0.02867 -0.0723 0.1395 1.0000
12.500 1.6116 0.03787 0.03029 -0.0709 0.1342 1.0000
12.750 1.6154 0.03973 0.03211 -0.0693 0.1296 1.0000
13.000 1.6236 0.04127 0.03384 -0.0681 0.1247 1.0000
13.250 1.6284 0.04313 0.03577 -0.0670 0.1200 1.0000
13.500 1.6310 0.04523 0.03788 -0.0657 0.1157 1.0000
13.750 1.6361 0.04718 0.04000 -0.0647 0.1107 1.0000
14.000 1.6364 0.04960 0.04246 -0.0637 0.1061 1.0000
14.250 1.6375 0.05205 0.04501 -0.0629 0.1012 1.0000
14.500 1.6369 0.05478 0.04783 -0.0622 0.0959 1.0000
14.750 1.6327 0.05790 0.05098 -0.0614 0.0908 1.0000
15.000 1.6296 0.06113 0.05435 -0.0611 0.0849 1.0000
15.250 1.6219 0.06484 0.05805 -0.0605 0.0796 1.0000
15.500 1.6165 0.06857 0.06194 -0.0605 0.0738 1.0000
15.750 1.6079 0.07261 0.06600 -0.0604 0.0692 1.0000
16.000 1.6030 0.07653 0.07008 -0.0608 0.0642 1.0000
16.250 1.5947 0.08075 0.07428 -0.0611 0.0609 1.0000
16.500 1.5908 0.08468 0.07840 -0.0616 0.0571 1.0000
16.750 1.5850 0.08887 0.08267 -0.0624 0.0543 1.0000
17.000 1.5778 0.09319 0.08700 -0.0631 0.0521 1.0000
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