GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 422 AIRFOIL (goe422-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.32 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe422-il-1000000.txt Download as CSV file: xf-goe422-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 422 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4463 0.03335 0.03024 -0.1498 0.8513 0.0279
-11.750 -0.4447 0.03102 0.02766 -0.1504 0.8363 0.0281
-11.500 -0.4376 0.02893 0.02532 -0.1507 0.8251 0.0282
-11.250 -0.4277 0.02685 0.02302 -0.1508 0.8173 0.0284
-11.000 -0.4141 0.02514 0.02108 -0.1506 0.8100 0.0285
-10.750 -0.3976 0.02368 0.01941 -0.1503 0.8039 0.0286
-10.500 -0.3787 0.02238 0.01795 -0.1501 0.7989 0.0288
-10.250 -0.3586 0.02124 0.01664 -0.1498 0.7937 0.0290
-10.000 -0.3373 0.02026 0.01548 -0.1494 0.7884 0.0291
-9.750 -0.3147 0.01935 0.01443 -0.1492 0.7841 0.0293
-9.500 -0.2912 0.01851 0.01348 -0.1489 0.7802 0.0295
-9.250 -0.2671 0.01777 0.01262 -0.1487 0.7757 0.0297
-9.000 -0.2425 0.01714 0.01186 -0.1484 0.7713 0.0298
-8.750 -0.2172 0.01661 0.01119 -0.1482 0.7665 0.0300
-8.500 -0.1912 0.01608 0.01060 -0.1480 0.7632 0.0302
-8.250 -0.1648 0.01565 0.01008 -0.1479 0.7593 0.0303
-8.000 -0.1408 0.01469 0.00902 -0.1475 0.7550 0.0306
-7.750 -0.1158 0.01400 0.00826 -0.1472 0.7508 0.0310
-7.500 -0.0895 0.01357 0.00778 -0.1471 0.7464 0.0313
-7.250 -0.0625 0.01318 0.00738 -0.1470 0.7429 0.0316
-7.000 -0.0352 0.01287 0.00705 -0.1469 0.7387 0.0320
-6.750 -0.0079 0.01259 0.00673 -0.1468 0.7344 0.0324
-6.500 0.0192 0.01232 0.00639 -0.1466 0.7298 0.0328
-6.250 0.0466 0.01202 0.00605 -0.1465 0.7257 0.0332
-6.000 0.0741 0.01172 0.00573 -0.1464 0.7215 0.0335
-5.750 0.1016 0.01146 0.00543 -0.1463 0.7164 0.0339
-5.500 0.1287 0.01127 0.00516 -0.1461 0.7105 0.0341
-5.250 0.1561 0.01100 0.00485 -0.1459 0.7048 0.0345
-5.000 0.1824 0.01059 0.00442 -0.1457 0.6980 0.0351
-4.750 0.2091 0.01039 0.00417 -0.1454 0.6910 0.0357
-4.500 0.2370 0.01019 0.00397 -0.1453 0.6854 0.0364
-4.250 0.2647 0.01003 0.00379 -0.1452 0.6794 0.0371
-4.000 0.2919 0.00991 0.00361 -0.1450 0.6730 0.0378
-3.750 0.3200 0.00978 0.00346 -0.1450 0.6673 0.0385
-3.500 0.3473 0.00957 0.00324 -0.1448 0.6610 0.0397
-3.250 0.3743 0.00947 0.00311 -0.1446 0.6544 0.0410
-3.000 0.4024 0.00937 0.00300 -0.1446 0.6485 0.0425
-2.750 0.4298 0.00926 0.00286 -0.1444 0.6412 0.0442
-2.500 0.4566 0.00918 0.00276 -0.1441 0.6338 0.0467
-2.250 0.4843 0.00908 0.00266 -0.1440 0.6262 0.0504
-2.000 0.5108 0.00902 0.00259 -0.1437 0.6180 0.0570
-1.750 0.5383 0.00892 0.00255 -0.1436 0.6108 0.0698
-1.500 0.5653 0.00892 0.00255 -0.1434 0.6025 0.0821
-1.250 0.5924 0.00893 0.00256 -0.1432 0.5948 0.0907
-1.000 0.6194 0.00893 0.00256 -0.1430 0.5864 0.0979
-0.750 0.6459 0.00898 0.00257 -0.1427 0.5783 0.1032
-0.500 0.6728 0.00897 0.00257 -0.1425 0.5696 0.1094
-0.250 0.6986 0.00905 0.00259 -0.1421 0.5600 0.1139
0.000 0.7244 0.00907 0.00260 -0.1417 0.5485 0.1216
0.250 0.7502 0.00912 0.00262 -0.1413 0.5382 0.1306
0.500 0.7753 0.00912 0.00266 -0.1408 0.5285 0.1562
0.750 0.8009 0.00893 0.00275 -0.1406 0.5207 0.2614
1.000 0.8260 0.00885 0.00284 -0.1402 0.5122 0.3409
1.250 0.8508 0.00864 0.00296 -0.1399 0.5044 0.4810
1.500 0.8743 0.00826 0.00314 -0.1393 0.4963 0.6946
1.750 0.8974 0.00828 0.00330 -0.1383 0.4880 0.7851
2.000 0.9221 0.00829 0.00340 -0.1376 0.4798 0.8255
2.250 0.9437 0.00835 0.00354 -0.1363 0.4709 0.8710
2.500 0.9808 0.00836 0.00368 -0.1382 0.4613 1.0000
2.750 1.0030 0.00857 0.00381 -0.1372 0.4512 1.0000
3.000 1.0243 0.00877 0.00393 -0.1360 0.4394 1.0000
3.250 1.0456 0.00898 0.00407 -0.1348 0.4286 1.0000
3.500 1.0657 0.00924 0.00425 -0.1334 0.4172 1.0000
3.750 1.0879 0.00946 0.00441 -0.1324 0.4068 1.0000
4.000 1.1089 0.00973 0.00461 -0.1313 0.3970 1.0000
4.250 1.1303 0.01000 0.00481 -0.1302 0.3871 1.0000
4.500 1.1518 0.01027 0.00503 -0.1292 0.3784 1.0000
4.750 1.1729 0.01056 0.00527 -0.1281 0.3696 1.0000
5.000 1.1942 0.01085 0.00551 -0.1271 0.3621 1.0000
5.250 1.2157 0.01114 0.00576 -0.1262 0.3549 1.0000
5.500 1.2358 0.01149 0.00606 -0.1250 0.3477 1.0000
5.750 1.2582 0.01175 0.00630 -0.1243 0.3426 1.0000
6.000 1.2788 0.01208 0.00660 -0.1232 0.3367 1.0000
6.250 1.2985 0.01246 0.00694 -0.1221 0.3307 1.0000
6.500 1.3209 0.01273 0.00721 -0.1214 0.3264 1.0000
6.750 1.3412 0.01309 0.00754 -0.1204 0.3213 1.0000
7.000 1.3600 0.01352 0.00794 -0.1192 0.3159 1.0000
7.250 1.3811 0.01385 0.00827 -0.1184 0.3120 1.0000
7.500 1.4020 0.01420 0.00862 -0.1175 0.3072 1.0000
7.750 1.4208 0.01465 0.00905 -0.1164 0.3025 1.0000
8.000 1.4384 0.01517 0.00954 -0.1151 0.2973 1.0000
8.250 1.4598 0.01550 0.00989 -0.1145 0.2937 1.0000
8.500 1.4785 0.01598 0.01036 -0.1134 0.2885 1.0000
8.750 1.4943 0.01661 0.01096 -0.1120 0.2818 1.0000
9.000 1.5136 0.01708 0.01143 -0.1111 0.2761 1.0000
9.250 1.5287 0.01778 0.01209 -0.1097 0.2679 1.0000
9.500 1.5450 0.01843 0.01272 -0.1085 0.2595 1.0000
9.750 1.5573 0.01933 0.01356 -0.1069 0.2486 1.0000
10.000 1.5672 0.02040 0.01456 -0.1050 0.2329 1.0000
10.250 1.5689 0.02202 0.01602 -0.1023 0.2072 1.0000
10.500 1.5485 0.02519 0.01889 -0.0974 0.1602 1.0000
10.750 1.5304 0.02844 0.02192 -0.0932 0.1212 1.0000
11.000 1.5222 0.03113 0.02448 -0.0903 0.0973 1.0000
11.250 1.5300 0.03266 0.02600 -0.0889 0.0931 1.0000
11.500 1.5378 0.03425 0.02759 -0.0876 0.0906 1.0000
11.750 1.5465 0.03576 0.02913 -0.0864 0.0883 1.0000
12.000 1.5549 0.03736 0.03075 -0.0853 0.0866 1.0000
12.250 1.5654 0.03877 0.03220 -0.0844 0.0860 1.0000
12.500 1.5744 0.04034 0.03383 -0.0835 0.0854 1.0000
12.750 1.5835 0.04191 0.03545 -0.0826 0.0849 1.0000
13.000 1.5910 0.04369 0.03727 -0.0817 0.0843 1.0000
13.250 1.5986 0.04547 0.03910 -0.0808 0.0837 1.0000
13.500 1.6046 0.04744 0.04113 -0.0799 0.0832 1.0000
13.750 1.6101 0.04946 0.04320 -0.0791 0.0827 1.0000
14.000 1.6145 0.05163 0.04543 -0.0782 0.0821 1.0000
14.250 1.6177 0.05398 0.04783 -0.0774 0.0816 1.0000
14.500 1.6209 0.05635 0.05026 -0.0767 0.0810 1.0000
14.750 1.6222 0.05897 0.05294 -0.0760 0.0805 1.0000
15.000 1.6226 0.06171 0.05575 -0.0753 0.0800 1.0000
15.250 1.6223 0.06455 0.05866 -0.0747 0.0794 1.0000
15.500 1.6192 0.06779 0.06197 -0.0741 0.0788 1.0000
15.750 1.6146 0.07124 0.06551 -0.0736 0.0781 1.0000
16.250 1.6106 0.07758 0.07200 -0.0729 0.0773 1.0000
16.500 1.6106 0.08058 0.07507 -0.0727 0.0770 1.0000
16.750 1.6109 0.08352 0.07809 -0.0725 0.0768 1.0000
17.000 1.6089 0.08681 0.08146 -0.0725 0.0766 1.0000
17.250 1.6076 0.09002 0.08474 -0.0725 0.0763 1.0000
17.500 1.6060 0.09325 0.08804 -0.0725 0.0759 1.0000
17.750 1.6029 0.09671 0.09157 -0.0726 0.0755 1.0000
18.000 1.6014 0.09996 0.09489 -0.0728 0.0752 1.0000
18.250 1.5975 0.10356 0.09857 -0.0731 0.0749 1.0000
18.500 1.5959 0.10685 0.10193 -0.0734 0.0745 1.0000
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Polar data table (+)
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