GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Reynolds number: 500,000 Max Cl/Cd: 113.23 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe332-il-500000-n5.txt Download as CSV file: xf-goe332-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.0812 0.08537 0.08229 -0.0876 0.8258 0.0209
-8.750 -0.0742 0.08260 0.07946 -0.0891 0.8131 0.0215
-8.500 -0.0683 0.07952 0.07633 -0.0908 0.8026 0.0218
-8.250 -0.0628 0.07631 0.07307 -0.0928 0.7924 0.0219
-8.000 -0.0575 0.07296 0.06969 -0.0951 0.7828 0.0221
-7.750 -0.0538 0.06938 0.06607 -0.0982 0.7735 0.0223
-7.500 -0.0474 0.06249 0.05913 -0.1075 0.7645 0.0234
-7.250 -0.0309 0.06057 0.05716 -0.1097 0.7563 0.0236
-7.000 -0.0138 0.05741 0.05396 -0.1137 0.7479 0.0239
-6.750 0.0043 0.05340 0.04986 -0.1188 0.7400 0.0240
-6.500 0.0246 0.04935 0.04571 -0.1239 0.7319 0.0242
-6.000 0.0698 0.04060 0.03668 -0.1333 0.7168 0.0248
-5.750 0.0938 0.03530 0.03113 -0.1378 0.7096 0.0255
-5.500 0.1106 0.01961 0.01406 -0.1443 0.7047 0.0262
-5.250 0.1357 0.01782 0.01187 -0.1445 0.6972 0.0267
-5.000 0.1618 0.01677 0.01052 -0.1445 0.6905 0.0271
-4.750 0.1885 0.01590 0.00941 -0.1445 0.6835 0.0273
-4.500 0.2151 0.01525 0.00854 -0.1444 0.6767 0.0275
-4.250 0.2419 0.01434 0.00745 -0.1444 0.6705 0.0278
-4.000 0.2688 0.01372 0.00671 -0.1443 0.6639 0.0281
-3.750 0.2958 0.01330 0.00618 -0.1443 0.6580 0.0284
-3.500 0.3233 0.01291 0.00573 -0.1442 0.6520 0.0287
-3.250 0.3506 0.01259 0.00532 -0.1442 0.6459 0.0291
-3.000 0.3781 0.01230 0.00495 -0.1441 0.6405 0.0294
-2.750 0.4057 0.01203 0.00462 -0.1440 0.6344 0.0298
-2.500 0.4329 0.01180 0.00431 -0.1439 0.6281 0.0302
-2.250 0.4605 0.01159 0.00406 -0.1438 0.6220 0.0308
-2.000 0.4880 0.01141 0.00384 -0.1437 0.6154 0.0315
-1.500 0.5431 0.01110 0.00343 -0.1436 0.6049 0.0325
-1.250 0.5708 0.01094 0.00325 -0.1435 0.5996 0.0329
-1.000 0.5982 0.01076 0.00304 -0.1435 0.5946 0.0337
-0.750 0.6260 0.01064 0.00293 -0.1435 0.5898 0.0346
-0.500 0.6538 0.01056 0.00284 -0.1435 0.5846 0.0355
-0.250 0.6812 0.01051 0.00277 -0.1434 0.5794 0.0366
0.000 0.7088 0.01048 0.00271 -0.1433 0.5745 0.0379
0.250 0.7366 0.01044 0.00267 -0.1433 0.5687 0.0399
0.500 0.7639 0.01041 0.00263 -0.1432 0.5633 0.0432
0.750 0.7914 0.01039 0.00261 -0.1431 0.5583 0.0481
1.000 0.8189 0.01027 0.00264 -0.1432 0.5523 0.0913
1.250 0.8458 0.01028 0.00270 -0.1430 0.5459 0.1213
1.500 0.8732 0.01030 0.00275 -0.1429 0.5396 0.1382
1.750 0.9002 0.01033 0.00281 -0.1428 0.5329 0.1553
2.000 0.9269 0.01035 0.00287 -0.1427 0.5266 0.1797
2.250 0.9539 0.00992 0.00304 -0.1430 0.5193 0.4396
2.750 1.0004 0.00907 0.00329 -0.1410 0.5033 1.0000
3.000 1.0262 0.00923 0.00338 -0.1407 0.4950 1.0000
3.250 1.0525 0.00937 0.00348 -0.1404 0.4864 1.0000
3.500 1.0780 0.00954 0.00359 -0.1400 0.4777 1.0000
3.750 1.1029 0.00974 0.00373 -0.1395 0.4662 1.0000
4.000 1.1274 0.00996 0.00387 -0.1389 0.4526 1.0000
4.250 1.1513 0.01020 0.00404 -0.1383 0.4384 1.0000
4.500 1.1751 0.01046 0.00423 -0.1376 0.4253 1.0000
4.750 1.1988 0.01072 0.00442 -0.1369 0.4139 1.0000
5.000 1.2222 0.01099 0.00463 -0.1362 0.4027 1.0000
5.250 1.2459 0.01124 0.00485 -0.1356 0.3918 1.0000
5.500 1.2689 0.01152 0.00509 -0.1348 0.3815 1.0000
5.750 1.2916 0.01181 0.00533 -0.1340 0.3717 1.0000
6.000 1.3148 0.01207 0.00558 -0.1332 0.3633 1.0000
6.250 1.3369 0.01237 0.00585 -0.1323 0.3551 1.0000
6.500 1.3597 0.01263 0.00611 -0.1315 0.3476 1.0000
6.750 1.3805 0.01297 0.00642 -0.1304 0.3388 1.0000
7.000 1.4023 0.01325 0.00671 -0.1295 0.3312 1.0000
7.250 1.4214 0.01360 0.00704 -0.1280 0.3232 1.0000
7.500 1.4409 0.01392 0.00736 -0.1267 0.3145 1.0000
7.750 1.4579 0.01435 0.00775 -0.1249 0.3039 1.0000
8.000 1.4756 0.01477 0.00816 -0.1233 0.2930 1.0000
8.250 1.4932 0.01520 0.00858 -0.1217 0.2825 1.0000
8.500 1.5088 0.01573 0.00907 -0.1198 0.2695 1.0000
8.750 1.5233 0.01632 0.00961 -0.1178 0.2554 1.0000
9.000 1.5365 0.01699 0.01023 -0.1157 0.2390 1.0000
9.250 1.5482 0.01775 0.01093 -0.1134 0.2219 1.0000
9.500 1.5572 0.01869 0.01178 -0.1108 0.2029 1.0000
9.750 1.5629 0.01986 0.01283 -0.1079 0.1807 1.0000
10.000 1.5665 0.02122 0.01409 -0.1049 0.1603 1.0000
10.250 1.5724 0.02251 0.01532 -0.1024 0.1451 1.0000
10.500 1.5776 0.02393 0.01668 -0.1000 0.1272 1.0000
10.750 1.5746 0.02601 0.01861 -0.0970 0.0998 1.0000
11.000 1.5747 0.02800 0.02053 -0.0946 0.0853 1.0000
11.250 1.5791 0.02973 0.02227 -0.0927 0.0761 1.0000
11.500 1.5832 0.03154 0.02410 -0.0910 0.0672 1.0000
11.750 1.5713 0.03482 0.02722 -0.0883 0.0382 1.0000
12.000 1.5637 0.03785 0.03022 -0.0861 0.0266 1.0000
12.250 1.5653 0.04013 0.03255 -0.0848 0.0229 1.0000
12.500 1.5683 0.04235 0.03483 -0.0836 0.0208 1.0000
12.750 1.5713 0.04460 0.03716 -0.0825 0.0192 1.0000
13.000 1.5729 0.04705 0.03968 -0.0815 0.0180 1.0000
13.250 1.5756 0.04945 0.04216 -0.0807 0.0170 1.0000
13.500 1.5781 0.05192 0.04471 -0.0799 0.0162 1.0000
13.750 1.5793 0.05458 0.04745 -0.0792 0.0155 1.0000
14.000 1.5791 0.05743 0.05038 -0.0785 0.0148 1.0000
14.250 1.5771 0.06057 0.05360 -0.0779 0.0142 1.0000
14.500 1.5770 0.06355 0.05667 -0.0775 0.0138 1.0000
14.750 1.5765 0.06662 0.05984 -0.0772 0.0134 1.0000
15.000 1.5750 0.06983 0.06316 -0.0769 0.0131 1.0000
15.250 1.5729 0.07317 0.06660 -0.0767 0.0127 1.0000
15.500 1.5699 0.07670 0.07022 -0.0766 0.0124 1.0000
15.750 1.5657 0.08045 0.07406 -0.0766 0.0121 1.0000
16.000 1.5607 0.08435 0.07805 -0.0767 0.0118 1.0000
16.250 1.5542 0.08849 0.08229 -0.0770 0.0115 1.0000
16.500 1.5461 0.09295 0.08685 -0.0774 0.0113 1.0000
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Polar data table (+)
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