GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 200,000 Max Cl/Cd: 71.69 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe331-il-200000-n5.txt Download as CSV file: xf-goe331-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0520 0.09316 0.08943 -0.0774 0.9145 0.0256
-8.500 -0.0436 0.09054 0.08679 -0.0797 0.9001 0.0262
-8.250 -0.0370 0.08808 0.08429 -0.0825 0.8856 0.0263
-7.750 -0.0187 0.08240 0.07854 -0.0847 0.8642 0.0266
-7.500 -0.0094 0.07981 0.07592 -0.0853 0.8545 0.0268
-7.250 0.0016 0.07721 0.07328 -0.0870 0.8461 0.0271
-7.000 0.0145 0.07456 0.07057 -0.0893 0.8379 0.0275
-6.750 0.0290 0.07184 0.06780 -0.0922 0.8309 0.0279
-6.500 0.0452 0.06907 0.06498 -0.0956 0.8235 0.0285
-6.250 0.0674 0.06602 0.06183 -0.1015 0.8172 0.0296
-6.000 0.0968 0.06261 0.05829 -0.1102 0.8102 0.0298
-5.750 0.1116 0.05985 0.05551 -0.1104 0.8044 0.0300
-5.250 0.1490 0.05476 0.05032 -0.1135 0.7921 0.0308
-5.000 0.1721 0.05220 0.04766 -0.1161 0.7854 0.0314
-4.750 0.1976 0.04960 0.04495 -0.1191 0.7791 0.0323
-4.500 0.2393 0.04653 0.04156 -0.1257 0.7719 0.0338
-4.250 0.2563 0.04415 0.03916 -0.1257 0.7658 0.0341
-4.000 0.2783 0.04204 0.03700 -0.1267 0.7592 0.0347
-3.750 0.3035 0.03997 0.03482 -0.1281 0.7525 0.0355
-3.500 0.3319 0.03789 0.03256 -0.1297 0.7469 0.0368
-3.250 0.3691 0.03575 0.03005 -0.1321 0.7404 0.0383
-3.000 0.3903 0.03373 0.02802 -0.1325 0.7336 0.0388
-2.750 0.4152 0.03209 0.02628 -0.1331 0.7275 0.0398
-2.250 0.4716 0.02891 0.02272 -0.1343 0.7134 0.0444
-2.000 0.4975 0.02761 0.02132 -0.1346 0.7060 0.0463
-1.750 0.5281 0.02632 0.01971 -0.1348 0.6983 0.0498
-1.500 0.5529 0.02503 0.01837 -0.1350 0.6897 0.0514
-1.250 0.5822 0.02411 0.01714 -0.1350 0.6809 0.0566
-1.000 0.6074 0.02295 0.01595 -0.1351 0.6723 0.0589
-0.750 0.6355 0.02210 0.01488 -0.1350 0.6644 0.0653
0.500 0.7742 0.01773 0.00949 -0.1332 0.6158 0.0467
0.750 0.8015 0.01707 0.00863 -0.1326 0.6047 0.0414
1.000 0.8282 0.01655 0.00789 -0.1319 0.5926 0.0391
1.250 0.8541 0.01627 0.00740 -0.1312 0.5790 0.0379
1.500 0.8793 0.01598 0.00699 -0.1306 0.5637 0.0380
1.750 0.9038 0.01568 0.00664 -0.1300 0.5475 0.0392
2.000 0.9280 0.01553 0.00640 -0.1293 0.5305 0.0398
2.250 0.9519 0.01543 0.00620 -0.1284 0.5131 0.0395
2.500 0.9753 0.01539 0.00607 -0.1276 0.4945 0.0394
2.750 0.9983 0.01541 0.00601 -0.1267 0.4741 0.0395
3.000 1.0204 0.01551 0.00602 -0.1257 0.4515 0.0398
3.250 1.0414 0.01569 0.00608 -0.1245 0.4281 0.0402
3.500 1.0623 0.01594 0.00620 -0.1234 0.4057 0.0413
3.750 1.0828 0.01625 0.00638 -0.1222 0.3876 0.0433
4.000 1.1037 0.01653 0.00655 -0.1211 0.3739 0.0447
4.250 1.1244 0.01687 0.00679 -0.1200 0.3635 0.0458
4.500 1.1462 0.01716 0.00703 -0.1190 0.3549 0.0475
4.750 1.1668 0.01753 0.00731 -0.1179 0.3477 0.0497
5.000 1.1888 0.01782 0.00761 -0.1170 0.3417 0.0581
5.250 1.2079 0.01685 0.00808 -0.1156 0.3364 1.0000
5.500 1.2281 0.01730 0.00844 -0.1144 0.3313 1.0000
5.750 1.2495 0.01768 0.00878 -0.1134 0.3267 1.0000
6.000 1.2706 0.01806 0.00913 -0.1124 0.3220 1.0000
6.250 1.2903 0.01848 0.00952 -0.1112 0.3179 1.0000
6.500 1.3094 0.01895 0.00993 -0.1099 0.3145 1.0000
6.750 1.3297 0.01939 0.01035 -0.1088 0.3114 1.0000
7.000 1.3506 0.01977 0.01077 -0.1079 0.3081 1.0000
7.250 1.3710 0.02019 0.01123 -0.1069 0.3050 1.0000
7.500 1.3909 0.02065 0.01170 -0.1058 0.3019 1.0000
7.750 1.4104 0.02116 0.01219 -0.1048 0.2990 1.0000
8.000 1.4301 0.02171 0.01272 -0.1037 0.2960 1.0000
8.250 1.4496 0.02215 0.01324 -0.1027 0.2928 1.0000
8.500 1.4685 0.02262 0.01378 -0.1016 0.2892 1.0000
8.750 1.4867 0.02313 0.01436 -0.1004 0.2856 1.0000
9.000 1.5044 0.02369 0.01494 -0.0992 0.2823 1.0000
9.250 1.5223 0.02432 0.01554 -0.0981 0.2790 1.0000
9.500 1.5394 0.02485 0.01619 -0.0968 0.2756 1.0000
9.750 1.5563 0.02542 0.01688 -0.0956 0.2720 1.0000
10.000 1.5731 0.02602 0.01757 -0.0944 0.2689 1.0000
10.250 1.5897 0.02666 0.01827 -0.0932 0.2663 1.0000
10.500 1.6064 0.02734 0.01900 -0.0921 0.2638 1.0000
10.750 1.6235 0.02803 0.01974 -0.0910 0.2613 1.0000
11.000 1.6387 0.02873 0.02060 -0.0898 0.2584 1.0000
11.250 1.6524 0.02949 0.02150 -0.0884 0.2546 1.0000
11.500 1.6640 0.03036 0.02246 -0.0869 0.2502 1.0000
11.750 1.6745 0.03133 0.02343 -0.0853 0.2458 1.0000
12.000 1.6851 0.03231 0.02461 -0.0839 0.2406 1.0000
12.250 1.6945 0.03340 0.02581 -0.0825 0.2352 1.0000
12.500 1.7016 0.03467 0.02711 -0.0809 0.2302 1.0000
12.750 1.7104 0.03591 0.02854 -0.0797 0.2229 1.0000
13.000 1.7143 0.03752 0.03018 -0.0781 0.2156 1.0000
13.250 1.7212 0.03902 0.03183 -0.0769 0.2070 1.0000
13.500 1.7242 0.04085 0.03371 -0.0756 0.1996 1.0000
13.750 1.7300 0.04255 0.03553 -0.0745 0.1905 1.0000
14.000 1.7319 0.04464 0.03769 -0.0733 0.1803 1.0000
14.250 1.7307 0.04711 0.04019 -0.0722 0.1680 1.0000
14.500 1.7263 0.05001 0.04310 -0.0711 0.1541 1.0000
14.750 1.7184 0.05337 0.04646 -0.0700 0.1408 1.0000
15.000 1.7083 0.05713 0.05022 -0.0691 0.1292 1.0000
15.250 1.6967 0.06123 0.05434 -0.0685 0.1193 1.0000
15.500 1.6850 0.06550 0.05866 -0.0681 0.1100 1.0000
15.750 1.6733 0.06993 0.06316 -0.0679 0.1008 1.0000
16.000 1.6593 0.07483 0.06813 -0.0680 0.0909 1.0000
16.250 1.6415 0.08041 0.07377 -0.0684 0.0787 1.0000
16.500 1.6192 0.08681 0.08019 -0.0693 0.0674 1.0000
16.750 1.5963 0.09353 0.08696 -0.0705 0.0595 1.0000
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Polar data table (+)
Polar graphs
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