GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 200,000 Max Cl/Cd: 81.23 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe301-il-200000.txt Download as CSV file: xf-goe301-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2503 0.11559 0.11211 -0.0330 1.0000 0.0357
-9.250 -0.2617 0.11503 0.11163 -0.0328 1.0000 0.0359
-9.000 -0.2765 0.11461 0.11129 -0.0317 1.0000 0.0360
-8.500 -0.2653 0.10730 0.10405 -0.0274 1.0000 0.0367
-8.250 -0.2689 0.10556 0.10237 -0.0250 1.0000 0.0371
-8.000 -0.2757 0.10422 0.10111 -0.0227 0.9998 0.0376
-7.750 -0.2533 0.10024 0.09711 -0.0281 0.9957 0.0389
-7.500 -0.2318 0.09629 0.09316 -0.0341 0.9899 0.0404
-7.250 -0.1965 0.09203 0.08887 -0.0542 0.9761 0.0421
-7.000 -0.1698 0.08626 0.08308 -0.0591 0.9725 0.0426
-6.750 -0.1501 0.08222 0.07905 -0.0583 0.9657 0.0433
-6.500 -0.1184 0.07807 0.07487 -0.0639 0.9607 0.0451
-6.250 -0.0875 0.07392 0.07069 -0.0714 0.9506 0.0474
-6.000 -0.0280 0.06769 0.06424 -0.0942 0.9390 0.0498
-5.750 -0.0075 0.06359 0.06018 -0.0935 0.9348 0.0506
-5.500 0.0199 0.06019 0.05677 -0.0960 0.9281 0.0519
-5.250 0.0544 0.05664 0.05315 -0.1016 0.9192 0.0548
-5.000 0.1160 0.05139 0.04749 -0.1176 0.9069 0.0589
-4.750 0.1392 0.04781 0.04395 -0.1185 0.8980 0.0599
-4.500 0.1661 0.04511 0.04119 -0.1203 0.8858 0.0614
-4.250 0.1956 0.04261 0.03857 -0.1228 0.8710 0.0645
-4.000 0.2420 0.03917 0.03461 -0.1297 0.8562 0.0699
-3.750 0.2635 0.03665 0.03210 -0.1300 0.8414 0.0711
-3.500 0.2886 0.03471 0.03006 -0.1307 0.8270 0.0732
-3.250 0.3323 0.03474 0.02934 -0.1335 0.8133 0.0812
-3.000 0.3523 0.03048 0.02520 -0.1343 0.8012 0.0832
-2.750 0.3772 0.02891 0.02355 -0.1346 0.7889 0.0863
-2.500 0.4111 0.02780 0.02193 -0.1358 0.7762 0.0958
-2.250 0.4350 0.02583 0.01997 -0.1360 0.7645 0.0984
-2.000 0.4630 0.02483 0.01877 -0.1363 0.7540 0.1052
-1.750 0.4911 0.02347 0.01718 -0.1367 0.7430 0.1142
-1.500 0.5187 0.02261 0.01611 -0.1370 0.7320 0.1285
-1.250 0.5457 0.02177 0.01512 -0.1371 0.7220 0.1451
-1.000 0.5717 0.02092 0.01420 -0.1371 0.7112 0.1627
-0.750 0.5983 0.02033 0.01350 -0.1371 0.7010 0.1856
-0.500 0.6412 0.01768 0.00959 -0.1360 0.6927 0.0823
-0.250 0.6683 0.01694 0.00871 -0.1356 0.6821 0.0830
0.000 0.6965 0.01656 0.00811 -0.1352 0.6726 0.0820
0.250 0.7232 0.01593 0.00741 -0.1348 0.6618 0.0825
0.500 0.7499 0.01546 0.00689 -0.1344 0.6515 0.0847
0.750 0.7770 0.01523 0.00659 -0.1340 0.6416 0.0900
1.000 0.8031 0.01501 0.00634 -0.1334 0.6299 0.0937
1.250 0.8292 0.01462 0.00596 -0.1330 0.6189 0.0988
1.500 0.8559 0.01450 0.00578 -0.1325 0.6083 0.1082
1.750 0.8815 0.01427 0.00562 -0.1320 0.5963 0.1190
2.000 0.9080 0.01420 0.00555 -0.1316 0.5858 0.1380
2.250 0.9314 0.01255 0.00562 -0.1307 0.5765 1.0000
2.500 0.9575 0.01273 0.00561 -0.1301 0.5659 1.0000
2.750 0.9839 0.01293 0.00565 -0.1297 0.5566 1.0000
3.000 1.0097 0.01311 0.00574 -0.1292 0.5463 1.0000
3.250 1.0356 0.01331 0.00587 -0.1288 0.5366 1.0000
3.500 1.0617 0.01353 0.00595 -0.1284 0.5275 1.0000
3.750 1.0868 0.01372 0.00614 -0.1278 0.5170 1.0000
4.000 1.1124 0.01395 0.00628 -0.1273 0.5076 1.0000
4.250 1.1375 0.01417 0.00643 -0.1268 0.4976 1.0000
4.500 1.1625 0.01441 0.00666 -0.1262 0.4877 1.0000
4.750 1.1879 0.01470 0.00682 -0.1257 0.4790 1.0000
5.000 1.2122 0.01494 0.00709 -0.1251 0.4689 1.0000
5.250 1.2371 0.01525 0.00735 -0.1246 0.4602 1.0000
5.500 1.2615 0.01553 0.00762 -0.1240 0.4511 1.0000
5.750 1.2860 0.01587 0.00794 -0.1234 0.4427 1.0000
6.000 1.3101 0.01619 0.00822 -0.1228 0.4337 1.0000
6.250 1.3335 0.01651 0.00859 -0.1221 0.4241 1.0000
6.500 1.3577 0.01690 0.00889 -0.1215 0.4156 1.0000
6.750 1.3799 0.01720 0.00928 -0.1206 0.4060 1.0000
7.000 1.4035 0.01760 0.00965 -0.1199 0.3979 1.0000
7.250 1.4254 0.01792 0.01006 -0.1189 0.3886 1.0000
7.500 1.4480 0.01833 0.01046 -0.1181 0.3802 1.0000
7.750 1.4694 0.01869 0.01086 -0.1171 0.3711 1.0000
8.000 1.4906 0.01910 0.01133 -0.1160 0.3623 1.0000
8.250 1.5114 0.01950 0.01174 -0.1149 0.3536 1.0000
8.500 1.5312 0.01990 0.01224 -0.1137 0.3443 1.0000
8.750 1.5512 0.02038 0.01268 -0.1125 0.3359 1.0000
9.000 1.5690 0.02078 0.01322 -0.1109 0.3260 1.0000
9.250 1.5868 0.02128 0.01375 -0.1093 0.3170 1.0000
9.500 1.6031 0.02177 0.01427 -0.1075 0.3075 1.0000
9.750 1.6181 0.02229 0.01490 -0.1055 0.2973 1.0000
10.000 1.6305 0.02288 0.01548 -0.1031 0.2873 1.0000
10.250 1.6396 0.02350 0.01611 -0.1002 0.2766 1.0000
10.500 1.6481 0.02417 0.01687 -0.0973 0.2650 1.0000
10.750 1.6560 0.02498 0.01771 -0.0945 0.2538 1.0000
11.000 1.6627 0.02594 0.01866 -0.0917 0.2436 1.0000
11.250 1.6694 0.02693 0.01970 -0.0890 0.2330 1.0000
11.500 1.6759 0.02801 0.02086 -0.0866 0.2227 1.0000
11.750 1.6802 0.02929 0.02215 -0.0840 0.2132 1.0000
12.000 1.6852 0.03061 0.02353 -0.0817 0.2037 1.0000
12.250 1.6910 0.03198 0.02501 -0.0797 0.1954 1.0000
12.500 1.6940 0.03360 0.02666 -0.0777 0.1878 1.0000
12.750 1.6993 0.03515 0.02835 -0.0760 0.1794 1.0000
13.000 1.6999 0.03715 0.03037 -0.0743 0.1719 1.0000
13.250 1.7031 0.03906 0.03241 -0.0729 0.1629 1.0000
13.500 1.7032 0.04135 0.03478 -0.0716 0.1547 1.0000
13.750 1.6994 0.04414 0.03762 -0.0705 0.1462 1.0000
14.000 1.6962 0.04703 0.04059 -0.0696 0.1362 1.0000
14.250 1.6887 0.05051 0.04414 -0.0689 0.1257 1.0000
14.500 1.6771 0.05461 0.04828 -0.0684 0.1136 1.0000
14.750 1.6612 0.05945 0.05314 -0.0682 0.0966 1.0000
15.000 1.6393 0.06526 0.05884 -0.0684 0.0697 1.0000
15.250 1.6149 0.07154 0.06504 -0.0688 0.0594 1.0000
15.500 1.5909 0.07804 0.07155 -0.0696 0.0537 1.0000
15.750 1.5713 0.08416 0.07777 -0.0705 0.0493 1.0000
16.000 1.5509 0.09058 0.08427 -0.0718 0.0465 1.0000
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