GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Reynolds number: 200,000 Max Cl/Cd: 84.29 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe332-il-200000-n5.txt Download as CSV file: xf-goe332-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 332 (PFALZ 61) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1451 0.10352 0.09986 -0.0663 0.9613 0.0372
-9.250 -0.1420 0.09996 0.09631 -0.0735 0.9446 0.0389
-9.000 -0.1306 0.09579 0.09212 -0.0796 0.9304 0.0390
-8.750 -0.1143 0.09121 0.08751 -0.0844 0.9183 0.0392
-8.500 -0.0904 0.08752 0.08377 -0.0850 0.9097 0.0398
-8.250 -0.0688 0.08424 0.08044 -0.0876 0.8977 0.0405
-8.000 -0.0497 0.08122 0.07735 -0.0906 0.8833 0.0417
-7.750 -0.0352 0.07821 0.07427 -0.0938 0.8673 0.0438
-7.500 -0.0288 0.07418 0.07014 -0.1040 0.8482 0.0463
-7.250 -0.0125 0.06980 0.06565 -0.1118 0.8351 0.0465
-7.000 0.0055 0.06551 0.06121 -0.1178 0.8243 0.0466
-6.750 0.0183 0.06193 0.05759 -0.1192 0.8143 0.0469
-6.500 0.0324 0.05947 0.05507 -0.1191 0.8055 0.0473
-6.250 0.0481 0.05740 0.05296 -0.1194 0.7961 0.0480
-5.750 0.0938 0.04526 0.04035 -0.1324 0.7795 0.0387
-5.500 0.1147 0.04260 0.03755 -0.1342 0.7722 0.0382
-5.250 0.1374 0.03925 0.03403 -0.1365 0.7641 0.0377
-5.000 0.1622 0.03546 0.02994 -0.1390 0.7574 0.0373
-4.750 0.1877 0.03039 0.02444 -0.1416 0.7501 0.0379
-4.500 0.2128 0.02651 0.02008 -0.1429 0.7435 0.0377
-4.250 0.2384 0.02368 0.01678 -0.1436 0.7370 0.0376
-4.000 0.2646 0.02165 0.01430 -0.1439 0.7300 0.0378
-3.500 0.3184 0.01911 0.01106 -0.1440 0.7171 0.0383
-3.250 0.3457 0.01831 0.00996 -0.1439 0.7108 0.0388
-3.000 0.3727 0.01753 0.00900 -0.1439 0.7047 0.0397
-2.750 0.3996 0.01695 0.00836 -0.1438 0.6980 0.0406
-2.500 0.4270 0.01645 0.00772 -0.1437 0.6923 0.0413
-2.250 0.4540 0.01598 0.00716 -0.1436 0.6857 0.0418
-2.000 0.4812 0.01557 0.00666 -0.1434 0.6795 0.0425
-1.750 0.5085 0.01522 0.00622 -0.1432 0.6738 0.0433
-1.500 0.5354 0.01491 0.00587 -0.1430 0.6669 0.0442
-1.250 0.5627 0.01466 0.00553 -0.1428 0.6608 0.0452
-1.000 0.5896 0.01447 0.00529 -0.1426 0.6541 0.0464
-0.750 0.6165 0.01422 0.00504 -0.1424 0.6474 0.0488
-0.500 0.6437 0.01409 0.00486 -0.1423 0.6416 0.0514
-0.250 0.6706 0.01397 0.00473 -0.1421 0.6350 0.0538
0.000 0.6979 0.01386 0.00458 -0.1419 0.6292 0.0574
0.250 0.7251 0.01377 0.00450 -0.1418 0.6237 0.0649
0.500 0.7519 0.01365 0.00456 -0.1417 0.6174 0.1033
0.750 0.7789 0.01364 0.00459 -0.1415 0.6117 0.1423
1.000 0.8057 0.01364 0.00463 -0.1414 0.6058 0.1673
1.250 0.8323 0.01359 0.00467 -0.1412 0.5995 0.1986
1.750 0.8806 0.01211 0.00490 -0.1396 0.5876 1.0000
2.000 0.9069 0.01226 0.00494 -0.1393 0.5811 1.0000
2.250 0.9333 0.01241 0.00499 -0.1390 0.5753 1.0000
2.500 0.9591 0.01255 0.00510 -0.1387 0.5681 1.0000
2.750 0.9851 0.01271 0.00517 -0.1383 0.5616 1.0000
3.000 1.0107 0.01286 0.00529 -0.1379 0.5541 1.0000
3.250 1.0362 0.01303 0.00541 -0.1374 0.5469 1.0000
3.500 1.0616 0.01319 0.00554 -0.1370 0.5398 1.0000
3.750 1.0866 0.01337 0.00569 -0.1365 0.5319 1.0000
4.000 1.1114 0.01355 0.00584 -0.1360 0.5239 1.0000
4.250 1.1359 0.01374 0.00600 -0.1354 0.5153 1.0000
4.500 1.1603 0.01394 0.00619 -0.1348 0.5071 1.0000
4.750 1.1843 0.01416 0.00638 -0.1341 0.4985 1.0000
5.000 1.2080 0.01438 0.00660 -0.1334 0.4893 1.0000
5.250 1.2310 0.01464 0.00680 -0.1326 0.4805 1.0000
5.500 1.2542 0.01488 0.00707 -0.1318 0.4707 1.0000
5.750 1.2762 0.01517 0.00732 -0.1309 0.4604 1.0000
6.000 1.2969 0.01549 0.00758 -0.1296 0.4483 1.0000
6.250 1.3169 0.01583 0.00789 -0.1283 0.4349 1.0000
6.500 1.3368 0.01618 0.00822 -0.1270 0.4224 1.0000
6.750 1.3567 0.01655 0.00857 -0.1257 0.4120 1.0000
7.000 1.3763 0.01694 0.00896 -0.1244 0.4032 1.0000
7.250 1.3965 0.01731 0.00936 -0.1232 0.3952 1.0000
7.500 1.4148 0.01774 0.00977 -0.1217 0.3870 1.0000
7.750 1.4326 0.01814 0.01021 -0.1201 0.3784 1.0000
8.250 1.4651 0.01906 0.01118 -0.1164 0.3618 1.0000
8.500 1.4807 0.01958 0.01171 -0.1145 0.3549 1.0000
8.750 1.4976 0.02006 0.01226 -0.1129 0.3478 1.0000
9.000 1.5112 0.02067 0.01289 -0.1108 0.3393 1.0000
9.250 1.5248 0.02128 0.01355 -0.1088 0.3293 1.0000
9.500 1.5354 0.02203 0.01430 -0.1064 0.3180 1.0000
9.750 1.5439 0.02291 0.01516 -0.1038 0.3057 1.0000
10.000 1.5538 0.02377 0.01606 -0.1016 0.2929 1.0000
10.250 1.5629 0.02474 0.01707 -0.0994 0.2802 1.0000
10.500 1.5702 0.02585 0.01820 -0.0971 0.2663 1.0000
10.750 1.5761 0.02713 0.01948 -0.0948 0.2515 1.0000
11.000 1.5802 0.02861 0.02094 -0.0926 0.2353 1.0000
11.250 1.5834 0.03025 0.02257 -0.0905 0.2194 1.0000
11.500 1.5844 0.03215 0.02446 -0.0883 0.2031 1.0000
11.750 1.5838 0.03428 0.02655 -0.0863 0.1874 1.0000
12.000 1.5819 0.03662 0.02886 -0.0844 0.1723 1.0000
12.250 1.5782 0.03920 0.03142 -0.0825 0.1565 1.0000
12.500 1.5742 0.04191 0.03410 -0.0808 0.1402 1.0000
12.750 1.5680 0.04494 0.03710 -0.0792 0.1211 1.0000
13.000 1.5574 0.04853 0.04059 -0.0777 0.1006 1.0000
13.250 1.5465 0.05231 0.04431 -0.0764 0.0865 1.0000
13.500 1.5383 0.05591 0.04791 -0.0754 0.0753 1.0000
13.750 1.5294 0.05971 0.05173 -0.0746 0.0571 1.0000
14.000 1.5100 0.06489 0.05676 -0.0738 0.0376 1.0000
14.250 1.4988 0.06925 0.06115 -0.0734 0.0324 1.0000
14.500 1.4914 0.07326 0.06525 -0.0731 0.0295 1.0000
14.750 1.4837 0.07742 0.06950 -0.0731 0.0275 1.0000
15.000 1.4766 0.08157 0.07375 -0.0731 0.0260 1.0000
15.250 1.4718 0.08548 0.07780 -0.0733 0.0248 1.0000
15.500 1.4657 0.08965 0.08210 -0.0736 0.0237 1.0000
15.750 1.4585 0.09406 0.08663 -0.0741 0.0229 1.0000
16.000 1.4499 0.09874 0.09142 -0.0748 0.0221 1.0000
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Polar data table (+)
Polar graphs
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