GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 200,000 Max Cl/Cd: 81.12 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe301-il-200000-n5.txt Download as CSV file: xf-goe301-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1632 0.09549 0.09205 -0.0565 0.9729 0.0308
-8.000 -0.1507 0.09175 0.08832 -0.0618 0.9636 0.0309
-7.750 -0.1367 0.08778 0.08436 -0.0654 0.9530 0.0310
-7.500 -0.1195 0.08440 0.08098 -0.0644 0.9476 0.0315
-7.250 -0.0992 0.08107 0.07764 -0.0677 0.9387 0.0324
-7.000 -0.0780 0.07779 0.07434 -0.0722 0.9273 0.0346
-6.750 -0.0425 0.07242 0.06886 -0.0890 0.9115 0.0366
-6.500 -0.0115 0.06747 0.06380 -0.0976 0.8975 0.0367
-6.250 0.0065 0.06399 0.06029 -0.0977 0.8836 0.0371
-6.000 0.0258 0.06156 0.05781 -0.0980 0.8677 0.0381
-5.750 0.0496 0.05896 0.05513 -0.1012 0.8500 0.0407
-5.500 0.0979 0.05364 0.04948 -0.1157 0.8299 0.0435
-5.250 0.1271 0.04979 0.04541 -0.1201 0.8110 0.0436
-4.750 0.1636 0.04498 0.04044 -0.1205 0.7749 0.0453
-4.500 0.2037 0.04034 0.03536 -0.1268 0.7603 0.0433
-4.250 0.2231 0.03842 0.03337 -0.1269 0.7463 0.0418
-4.000 0.2519 0.03546 0.03017 -0.1293 0.7342 0.0404
-3.750 0.2827 0.03276 0.02716 -0.1315 0.7234 0.0415
-3.500 0.3125 0.03015 0.02425 -0.1332 0.7133 0.0411
-3.250 0.3423 0.02762 0.02141 -0.1345 0.7039 0.0405
-2.750 0.4017 0.02335 0.01644 -0.1362 0.6867 0.0415
-2.250 0.4600 0.01993 0.01227 -0.1369 0.6702 0.0424
-2.000 0.4886 0.01864 0.01060 -0.1370 0.6626 0.0429
-1.750 0.5169 0.01760 0.00924 -0.1370 0.6546 0.0435
-1.500 0.5441 0.01701 0.00851 -0.1369 0.6466 0.0446
-1.250 0.5712 0.01669 0.00813 -0.1368 0.6382 0.0460
-1.000 0.5986 0.01625 0.00753 -0.1366 0.6302 0.0472
-0.750 0.6261 0.01575 0.00689 -0.1364 0.6223 0.0482
-0.500 0.6533 0.01534 0.00634 -0.1361 0.6141 0.0494
-0.250 0.6804 0.01498 0.00587 -0.1358 0.6056 0.0508
0.000 0.7072 0.01470 0.00553 -0.1355 0.5971 0.0527
0.250 0.7340 0.01457 0.00541 -0.1352 0.5882 0.0554
0.500 0.7606 0.01442 0.00521 -0.1349 0.5795 0.0581
0.750 0.7873 0.01426 0.00501 -0.1346 0.5696 0.0608
1.000 0.8136 0.01411 0.00486 -0.1342 0.5602 0.0639
1.250 0.8398 0.01406 0.00480 -0.1339 0.5490 0.0693
1.500 0.8659 0.01399 0.00472 -0.1335 0.5369 0.0752
1.750 0.8918 0.01399 0.00467 -0.1331 0.5249 0.0820
2.000 0.9175 0.01400 0.00464 -0.1327 0.5136 0.0911
2.250 0.9436 0.01403 0.00466 -0.1323 0.5028 0.1030
2.500 0.9695 0.01405 0.00474 -0.1320 0.4934 0.1326
3.000 1.0171 0.01290 0.00504 -0.1304 0.4746 1.0000
3.250 1.0422 0.01314 0.00515 -0.1298 0.4646 1.0000
3.500 1.0672 0.01338 0.00530 -0.1293 0.4545 1.0000
3.750 1.0923 0.01363 0.00548 -0.1288 0.4455 1.0000
4.000 1.1171 0.01390 0.00566 -0.1282 0.4371 1.0000
4.250 1.1422 0.01415 0.00587 -0.1278 0.4297 1.0000
4.500 1.1669 0.01443 0.00610 -0.1272 0.4219 1.0000
4.750 1.1914 0.01470 0.00634 -0.1267 0.4142 1.0000
5.000 1.2154 0.01500 0.00659 -0.1260 0.4054 1.0000
5.250 1.2395 0.01528 0.00687 -0.1254 0.3968 1.0000
5.500 1.2630 0.01559 0.00714 -0.1247 0.3885 1.0000
5.750 1.2870 0.01588 0.00744 -0.1241 0.3811 1.0000
6.000 1.3105 0.01618 0.00776 -0.1234 0.3739 1.0000
6.250 1.3336 0.01650 0.00808 -0.1227 0.3663 1.0000
6.500 1.3560 0.01683 0.00841 -0.1218 0.3571 1.0000
6.750 1.3785 0.01715 0.00876 -0.1210 0.3485 1.0000
7.000 1.4000 0.01752 0.00913 -0.1200 0.3403 1.0000
7.250 1.4219 0.01786 0.00952 -0.1191 0.3316 1.0000
7.500 1.4422 0.01827 0.00992 -0.1179 0.3237 1.0000
7.750 1.4634 0.01863 0.01036 -0.1169 0.3151 1.0000
8.000 1.4826 0.01907 0.01081 -0.1156 0.3071 1.0000
8.250 1.5021 0.01949 0.01128 -0.1143 0.2983 1.0000
8.500 1.5200 0.01997 0.01178 -0.1128 0.2903 1.0000
8.750 1.5367 0.02046 0.01232 -0.1111 0.2818 1.0000
9.000 1.5520 0.02098 0.01289 -0.1091 0.2742 1.0000
9.250 1.5667 0.02155 0.01350 -0.1071 0.2662 1.0000
9.500 1.5810 0.02217 0.01416 -0.1052 0.2588 1.0000
9.750 1.5946 0.02283 0.01489 -0.1031 0.2512 1.0000
10.000 1.6073 0.02356 0.01566 -0.1011 0.2443 1.0000
10.250 1.6192 0.02434 0.01650 -0.0990 0.2359 1.0000
10.500 1.6292 0.02524 0.01744 -0.0967 0.2266 1.0000
10.750 1.6358 0.02636 0.01855 -0.0942 0.2164 1.0000
11.000 1.6447 0.02742 0.01967 -0.0921 0.2052 1.0000
11.250 1.6519 0.02862 0.02092 -0.0899 0.1945 1.0000
11.500 1.6572 0.03002 0.02233 -0.0877 0.1838 1.0000
12.000 1.6663 0.03314 0.02552 -0.0838 0.1622 1.0000
12.250 1.6699 0.03491 0.02733 -0.0821 0.1535 1.0000
12.500 1.6708 0.03698 0.02944 -0.0804 0.1458 1.0000
12.750 1.6724 0.03911 0.03163 -0.0789 0.1380 1.0000
13.000 1.6706 0.04165 0.03421 -0.0775 0.1311 1.0000
13.250 1.6705 0.04414 0.03677 -0.0764 0.1244 1.0000
13.500 1.6658 0.04720 0.03988 -0.0754 0.1188 1.0000
13.750 1.6670 0.04971 0.04251 -0.0746 0.1127 1.0000
14.000 1.6618 0.05302 0.04589 -0.0740 0.1067 1.0000
14.250 1.6605 0.05597 0.04897 -0.0734 0.0992 1.0000
14.500 1.6556 0.05943 0.05250 -0.0731 0.0889 1.0000
14.750 1.6421 0.06406 0.05709 -0.0730 0.0681 1.0000
15.000 1.6221 0.06965 0.06261 -0.0732 0.0565 1.0000
15.250 1.6056 0.07497 0.06795 -0.0735 0.0490 1.0000
15.500 1.5899 0.08035 0.07340 -0.0741 0.0428 1.0000
15.750 1.5758 0.08564 0.07877 -0.0748 0.0370 1.0000
16.000 1.5622 0.09101 0.08423 -0.0757 0.0322 1.0000
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Polar data table (+)
Polar graphs
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