GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 100,000 Max Cl/Cd: 57.33 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe331-il-100000-n5.txt Download as CSV file: xf-goe331-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 331 (PFALZ 60) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0792 0.09822 0.09328 -0.0737 0.9461 0.0388
-8.250 -0.0662 0.09517 0.09023 -0.0755 0.9379 0.0396
-8.000 -0.0520 0.09216 0.08721 -0.0782 0.9302 0.0405
-7.750 -0.0430 0.08966 0.08472 -0.0802 0.9196 0.0418
-7.500 -0.0337 0.08742 0.08247 -0.0847 0.9090 0.0430
-7.250 -0.0208 0.08457 0.07961 -0.0891 0.8995 0.0435
-7.000 -0.0068 0.08128 0.07630 -0.0890 0.8933 0.0443
-6.750 0.0071 0.07850 0.07351 -0.0909 0.8854 0.0453
-6.500 0.0241 0.07563 0.07060 -0.0942 0.8787 0.0467
-6.250 0.0413 0.07298 0.06790 -0.0985 0.8702 0.0483
-6.000 0.0695 0.07015 0.06492 -0.1076 0.8629 0.0492
-5.750 0.0800 0.06712 0.06193 -0.1058 0.8564 0.0500
-5.500 0.0996 0.06432 0.05907 -0.1073 0.8515 0.0518
-5.250 0.1267 0.06198 0.05659 -0.1130 0.8440 0.0554
-5.000 0.1495 0.05900 0.05353 -0.1159 0.8380 0.0565
-4.750 0.1705 0.05620 0.05069 -0.1169 0.8339 0.0581
-4.500 0.1907 0.05410 0.04852 -0.1184 0.8263 0.0606
-4.250 0.2290 0.05182 0.04591 -0.1244 0.8206 0.0639
-4.000 0.2493 0.04888 0.04298 -0.1247 0.8167 0.0655
-3.750 0.2685 0.04707 0.04112 -0.1250 0.8085 0.0683
-3.500 0.3047 0.04504 0.03876 -0.1287 0.8025 0.0735
-3.250 0.3249 0.04275 0.03648 -0.1287 0.7960 0.0766
-3.000 0.3570 0.04143 0.03481 -0.1308 0.7877 0.0843
-2.750 0.3818 0.03887 0.03225 -0.1314 0.7820 0.0876
-2.500 0.4105 0.03816 0.03120 -0.1322 0.7726 0.0970
-2.250 0.4340 0.03566 0.02872 -0.1326 0.7662 0.1007
-2.000 0.4618 0.03460 0.02741 -0.1332 0.7581 0.1128
-1.750 0.4859 0.03282 0.02561 -0.1333 0.7503 0.1193
-1.500 0.5129 0.03141 0.02404 -0.1337 0.7429 0.1336
-1.000 0.5624 0.02886 0.02130 -0.1339 0.7255 0.1846
-0.500 0.6377 0.02655 0.01780 -0.1329 0.7099 0.0716
-0.250 0.6642 0.02541 0.01647 -0.1322 0.7010 0.0623
0.000 0.6938 0.02431 0.01516 -0.1322 0.6941 0.0585
0.250 0.7195 0.02372 0.01432 -0.1312 0.6842 0.0550
0.500 0.7475 0.02294 0.01340 -0.1310 0.6761 0.0540
0.750 0.7729 0.02243 0.01275 -0.1302 0.6660 0.0544
1.000 0.7993 0.02192 0.01211 -0.1296 0.6564 0.0546
1.250 0.8260 0.02137 0.01146 -0.1291 0.6465 0.0540
1.500 0.8505 0.02097 0.01100 -0.1282 0.6346 0.0534
1.750 0.8759 0.02057 0.01054 -0.1275 0.6229 0.0531
2.000 0.9015 0.02020 0.01010 -0.1268 0.6108 0.0530
2.250 0.9254 0.01993 0.00979 -0.1258 0.5973 0.0531
2.500 0.9488 0.01976 0.00956 -0.1247 0.5830 0.0543
2.750 0.9730 0.01966 0.00935 -0.1238 0.5677 0.0562
3.000 0.9970 0.01960 0.00919 -0.1230 0.5510 0.0578
3.250 1.0205 0.01964 0.00908 -0.1221 0.5332 0.0590
3.500 1.0435 0.01976 0.00904 -0.1211 0.5147 0.0606
3.750 1.0658 0.01996 0.00907 -0.1200 0.4959 0.0627
4.000 1.0876 0.02021 0.00920 -0.1189 0.4772 0.0676
4.250 1.1089 0.02050 0.00939 -0.1177 0.4590 0.0764
4.500 1.1265 0.01965 0.00982 -0.1162 0.4430 0.7671
5.000 1.1671 0.02036 0.01029 -0.1135 0.4137 1.0000
5.250 1.1873 0.02085 0.01064 -0.1123 0.4019 1.0000
5.500 1.2077 0.02136 0.01102 -0.1111 0.3922 1.0000
5.750 1.2283 0.02188 0.01143 -0.1101 0.3838 1.0000
6.000 1.2493 0.02241 0.01186 -0.1091 0.3769 1.0000
6.250 1.2704 0.02293 0.01233 -0.1082 0.3703 1.0000
6.500 1.2917 0.02349 0.01280 -0.1073 0.3646 1.0000
6.750 1.3130 0.02404 0.01333 -0.1065 0.3588 1.0000
7.000 1.3340 0.02460 0.01388 -0.1057 0.3533 1.0000
7.250 1.3561 0.02518 0.01441 -0.1050 0.3486 1.0000
7.500 1.3784 0.02576 0.01498 -0.1044 0.3443 1.0000
7.750 1.3994 0.02635 0.01563 -0.1036 0.3401 1.0000
8.000 1.4210 0.02695 0.01627 -0.1029 0.3361 1.0000
8.250 1.4441 0.02757 0.01688 -0.1025 0.3324 1.0000
8.500 1.4678 0.02823 0.01752 -0.1022 0.3287 1.0000
8.750 1.4859 0.02889 0.01832 -0.1010 0.3247 1.0000
9.000 1.5059 0.02957 0.01910 -0.1002 0.3209 1.0000
9.250 1.5277 0.03025 0.01983 -0.0996 0.3176 1.0000
9.500 1.5518 0.03093 0.02050 -0.0994 0.3139 1.0000
9.750 1.5668 0.03170 0.02143 -0.0979 0.3096 1.0000
10.000 1.5789 0.03249 0.02237 -0.0959 0.3047 1.0000
10.250 1.5947 0.03322 0.02316 -0.0945 0.3000 1.0000
10.500 1.6176 0.03391 0.02383 -0.0942 0.2959 1.0000
10.750 1.6261 0.03487 0.02503 -0.0919 0.2922 1.0000
11.000 1.6371 0.03583 0.02617 -0.0901 0.2883 1.0000
11.250 1.6510 0.03672 0.02721 -0.0886 0.2847 1.0000
11.500 1.6684 0.03754 0.02813 -0.0877 0.2814 1.0000
11.750 1.6894 0.03834 0.02898 -0.0872 0.2784 1.0000
12.000 1.6915 0.03969 0.03062 -0.0845 0.2750 1.0000
12.250 1.6969 0.04099 0.03215 -0.0823 0.2714 1.0000
12.500 1.7052 0.04216 0.03349 -0.0805 0.2676 1.0000
12.750 1.7188 0.04299 0.03438 -0.0793 0.2635 1.0000
13.000 1.7178 0.04460 0.03620 -0.0768 0.2591 1.0000
13.250 1.7115 0.04655 0.03840 -0.0741 0.2540 1.0000
13.500 1.7136 0.04787 0.03981 -0.0722 0.2482 1.0000
13.750 1.7076 0.04993 0.04204 -0.0701 0.2425 1.0000
14.000 1.6965 0.05257 0.04490 -0.0680 0.2360 1.0000
14.250 1.6937 0.05443 0.04678 -0.0664 0.2291 1.0000
14.500 1.6773 0.05810 0.05075 -0.0649 0.2225 1.0000
14.750 1.6711 0.06071 0.05342 -0.0639 0.2154 1.0000
15.000 1.6547 0.06500 0.05798 -0.0632 0.2085 1.0000
15.250 1.6448 0.06862 0.06172 -0.0628 0.2015 1.0000
15.500 1.6280 0.07355 0.06687 -0.0628 0.1948 1.0000
15.750 1.6133 0.07835 0.07181 -0.0632 0.1880 1.0000
16.000 1.5926 0.08436 0.07801 -0.0640 0.1819 1.0000
16.250 1.5692 0.09107 0.08490 -0.0654 0.1760 1.0000
16.500 1.5459 0.09802 0.09198 -0.0671 0.1704 1.0000
16.750 1.5064 0.10807 0.10224 -0.0703 0.1660 1.0000
17.000 1.4927 0.11379 0.10800 -0.0722 0.1593 1.0000
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Polar data table (+)
Polar graphs
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