GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Reynolds number: 100,000 Max Cl/Cd: 52.17 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe332-il-100000.txt Download as CSV file: xf-goe332-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2994 0.13158 0.12706 -0.0359 1.0000 0.0722
-9.500 -0.3241 0.13271 0.12832 -0.0326 1.0000 0.0723
-9.250 -0.3481 0.13362 0.12935 -0.0297 1.0000 0.0724
-9.000 -0.3110 0.12423 0.11992 -0.0266 0.9999 0.0741
-8.750 -0.2863 0.11967 0.11532 -0.0303 0.9958 0.0764
-8.500 -0.2660 0.11580 0.11144 -0.0352 0.9905 0.0792
-8.250 -0.2497 0.11267 0.10829 -0.0423 0.9842 0.0827
-8.000 -0.2539 0.11250 0.10815 -0.0528 0.9703 0.0842
-7.750 -0.2328 0.10642 0.10206 -0.0543 0.9651 0.0854
-7.500 -0.1980 0.10100 0.09659 -0.0551 0.9629 0.0887
-7.250 -0.1824 0.09786 0.09344 -0.0585 0.9544 0.0920
-7.000 -0.1693 0.09519 0.09076 -0.0666 0.9432 0.0962
-6.750 -0.1467 0.09105 0.08656 -0.0819 0.9326 0.0984
-6.500 -0.1355 0.08723 0.08278 -0.0771 0.9252 0.0998
-6.250 -0.1094 0.08340 0.07891 -0.0788 0.9207 0.1029
-6.000 -0.0912 0.08042 0.07590 -0.0826 0.9121 0.1071
-5.750 -0.0562 0.07605 0.07135 -0.0987 0.9040 0.1136
-5.250 -0.0189 0.06990 0.06522 -0.0978 0.8911 0.1207
-5.000 0.0304 0.06509 0.06015 -0.1123 0.8873 0.1295
-4.750 0.0348 0.06312 0.05823 -0.1091 0.8767 0.1314
-4.500 0.0718 0.05972 0.05474 -0.1136 0.8733 0.1385
-4.250 0.0955 0.05709 0.05190 -0.1186 0.8639 0.1460
-4.000 0.1233 0.05421 0.04903 -0.1198 0.8592 0.1513
-3.750 0.1662 0.05072 0.04534 -0.1261 0.8560 0.1641
-3.500 0.1853 0.04957 0.04396 -0.1277 0.8456 0.1772
-3.250 0.2162 0.04658 0.04100 -0.1290 0.8417 0.1836
-3.000 0.2587 0.04367 0.03792 -0.1335 0.8387 0.1995
-2.750 0.2702 0.04276 0.03691 -0.1323 0.8280 0.2129
-2.500 0.3074 0.04042 0.03447 -0.1350 0.8241 0.2330
-2.250 0.3266 0.03942 0.03339 -0.1347 0.8160 0.2619
-2.000 0.3912 0.03472 0.02753 -0.1416 0.8108 0.1487
-1.750 0.4418 0.03091 0.02276 -0.1444 0.8073 0.1090
-1.500 0.4661 0.02988 0.02148 -0.1439 0.7995 0.1065
-1.250 0.4988 0.02860 0.01988 -0.1444 0.7932 0.1053
-1.000 0.5393 0.02727 0.01824 -0.1459 0.7892 0.1082
-0.750 0.5570 0.02730 0.01809 -0.1441 0.7794 0.1116
-0.500 0.5928 0.02614 0.01685 -0.1450 0.7742 0.1162
-0.250 0.6173 0.02586 0.01655 -0.1442 0.7664 0.1224
0.000 0.6462 0.02529 0.01598 -0.1440 0.7594 0.1336
0.250 0.6833 0.02426 0.01499 -0.1448 0.7551 0.1634
0.500 0.6988 0.02397 0.01504 -0.1429 0.7450 0.2371
0.750 0.7311 0.02169 0.01450 -0.1426 0.7402 1.0000
1.000 0.7509 0.02225 0.01483 -0.1411 0.7311 1.0000
1.250 0.7828 0.02219 0.01454 -0.1413 0.7248 1.0000
1.500 0.8061 0.02257 0.01478 -0.1404 0.7166 1.0000
1.750 0.8346 0.02266 0.01472 -0.1402 0.7093 1.0000
2.000 0.8625 0.02281 0.01474 -0.1400 0.7024 1.0000
2.250 0.8867 0.02309 0.01493 -0.1392 0.6938 1.0000
2.500 0.9210 0.02293 0.01462 -0.1398 0.6883 1.0000
2.750 0.9393 0.02348 0.01516 -0.1382 0.6780 1.0000
3.000 0.9763 0.02318 0.01470 -0.1392 0.6730 1.0000
3.250 0.9918 0.02387 0.01543 -0.1373 0.6620 1.0000
3.500 1.0289 0.02357 0.01498 -0.1383 0.6568 1.0000
3.750 1.0445 0.02423 0.01569 -0.1363 0.6456 1.0000
4.000 1.0812 0.02397 0.01531 -0.1373 0.6401 1.0000
4.250 1.0966 0.02466 0.01606 -0.1354 0.6289 1.0000
4.500 1.1280 0.02464 0.01597 -0.1356 0.6220 1.0000
4.750 1.1487 0.02506 0.01643 -0.1344 0.6119 1.0000
5.000 1.1751 0.02530 0.01664 -0.1340 0.6037 1.0000
5.250 1.2001 0.02555 0.01689 -0.1334 0.5948 1.0000
5.500 1.2225 0.02597 0.01735 -0.1324 0.5857 1.0000
5.750 1.2514 0.02603 0.01738 -0.1324 0.5776 1.0000
6.000 1.2699 0.02663 0.01805 -0.1309 0.5679 1.0000
6.250 1.3020 0.02655 0.01794 -0.1313 0.5604 1.0000
6.500 1.3176 0.02722 0.01870 -0.1294 0.5500 1.0000
6.750 1.3546 0.02685 0.01823 -0.1304 0.5429 1.0000
7.000 1.3671 0.02753 0.01904 -0.1280 0.5316 1.0000
7.250 1.3930 0.02768 0.01922 -0.1275 0.5231 1.0000
7.500 1.4160 0.02795 0.01953 -0.1266 0.5140 1.0000
7.750 1.4355 0.02849 0.02015 -0.1253 0.5053 1.0000
8.000 1.4627 0.02863 0.02033 -0.1251 0.4972 1.0000
8.250 1.4784 0.02932 0.02113 -0.1233 0.4880 1.0000
8.500 1.5117 0.02916 0.02091 -0.1239 0.4799 1.0000
8.750 1.5214 0.03001 0.02194 -0.1211 0.4699 1.0000
9.000 1.5508 0.03006 0.02199 -0.1212 0.4614 1.0000
9.250 1.5650 0.03067 0.02273 -0.1191 0.4516 1.0000
9.500 1.5835 0.03117 0.02330 -0.1176 0.4422 1.0000
9.750 1.6163 0.03098 0.02304 -0.1181 0.4319 1.0000
10.000 1.6196 0.03179 0.02405 -0.1143 0.4207 1.0000
10.250 1.6323 0.03210 0.02440 -0.1118 0.4084 1.0000
10.500 1.6454 0.03224 0.02454 -0.1093 0.3951 1.0000
10.750 1.6579 0.03245 0.02472 -0.1067 0.3820 1.0000
11.000 1.6646 0.03291 0.02523 -0.1034 0.3703 1.0000
11.250 1.6606 0.03389 0.02636 -0.0987 0.3598 1.0000
11.500 1.6656 0.03460 0.02712 -0.0955 0.3488 1.0000
11.750 1.6743 0.03520 0.02770 -0.0929 0.3375 1.0000
12.000 1.6641 0.03674 0.02945 -0.0884 0.3272 1.0000
12.250 1.6619 0.03802 0.03083 -0.0850 0.3164 1.0000
12.500 1.6637 0.03918 0.03201 -0.0823 0.3054 1.0000
12.750 1.6539 0.04128 0.03432 -0.0790 0.2950 1.0000
13.000 1.6468 0.04336 0.03653 -0.0763 0.2840 1.0000
13.250 1.6399 0.04556 0.03880 -0.0739 0.2725 1.0000
13.500 1.6310 0.04809 0.04141 -0.0718 0.2606 1.0000
13.750 1.6166 0.05146 0.04492 -0.0700 0.2477 1.0000
14.000 1.6022 0.05507 0.04864 -0.0685 0.2338 1.0000
14.250 1.5873 0.05904 0.05269 -0.0674 0.2193 1.0000
14.500 1.5707 0.06350 0.05719 -0.0667 0.2038 1.0000
14.750 1.5515 0.06852 0.06220 -0.0663 0.1871 1.0000
15.000 1.5303 0.07413 0.06783 -0.0663 0.1690 1.0000
15.250 1.5071 0.08026 0.07392 -0.0666 0.1509 1.0000
15.500 1.4823 0.08687 0.08048 -0.0673 0.1331 1.0000
15.750 1.4575 0.09377 0.08733 -0.0684 0.1152 1.0000
16.000 1.4336 0.10070 0.09415 -0.0697 0.1018 1.0000
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