GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 423 AIRFOIL (goe423-il) Reynolds number: 500,000 Max Cl/Cd: 105.87 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe423-il-500000.txt Download as CSV file: xf-goe423-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 423 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2032 0.09897 0.09637 -0.0914 0.9634 0.0560
-11.500 -0.3242 0.06562 0.06292 -0.1148 0.9542 0.0552
-11.250 -0.3219 0.06357 0.06090 -0.1145 0.9435 0.0556
-11.000 -0.4818 0.03930 0.03581 -0.1271 0.9160 0.0515
-10.750 -0.5009 0.03488 0.03095 -0.1247 0.9044 0.0517
-10.500 -0.4972 0.03262 0.02844 -0.1229 0.8932 0.0523
-10.250 -0.4912 0.03036 0.02587 -0.1212 0.8832 0.0529
-10.000 -0.4827 0.02817 0.02334 -0.1194 0.8727 0.0534
-9.750 -0.4699 0.02642 0.02128 -0.1179 0.8617 0.0539
-9.500 -0.4537 0.02505 0.01961 -0.1166 0.8507 0.0544
-9.250 -0.4352 0.02412 0.01841 -0.1154 0.8381 0.0548
-9.000 -0.4178 0.02261 0.01663 -0.1143 0.8246 0.0555
-8.750 -0.3966 0.02135 0.01525 -0.1136 0.8100 0.0561
-8.500 -0.3742 0.02059 0.01437 -0.1129 0.7928 0.0566
-8.250 -0.3516 0.01997 0.01359 -0.1121 0.7716 0.0571
-8.000 -0.3292 0.01942 0.01287 -0.1112 0.7459 0.0577
-7.750 -0.3070 0.01892 0.01218 -0.1103 0.7155 0.0583
-7.500 -0.2848 0.01845 0.01149 -0.1094 0.6900 0.0589
-7.250 -0.2619 0.01802 0.01087 -0.1086 0.6721 0.0596
-7.000 -0.2382 0.01765 0.01032 -0.1079 0.6593 0.0604
-6.750 -0.2135 0.01727 0.00980 -0.1074 0.6500 0.0610
-6.500 -0.1888 0.01695 0.00932 -0.1069 0.6419 0.0615
-6.250 -0.1634 0.01652 0.00879 -0.1065 0.6356 0.0620
-6.000 -0.1387 0.01567 0.00789 -0.1061 0.6299 0.0629
-5.750 -0.1136 0.01526 0.00744 -0.1058 0.6247 0.0637
-5.500 -0.0879 0.01496 0.00710 -0.1054 0.6200 0.0646
-5.250 -0.0618 0.01466 0.00679 -0.1052 0.6161 0.0656
-5.000 -0.0356 0.01442 0.00650 -0.1049 0.6121 0.0667
-4.750 -0.0096 0.01420 0.00622 -0.1046 0.6082 0.0678
-4.500 0.0166 0.01402 0.00596 -0.1043 0.6043 0.0687
-4.250 0.0432 0.01385 0.00574 -0.1041 0.6009 0.0694
-4.000 0.0679 0.01336 0.00527 -0.1036 0.5980 0.0709
-3.750 0.0937 0.01310 0.00502 -0.1033 0.5951 0.0723
-3.500 0.1200 0.01291 0.00483 -0.1030 0.5922 0.0738
-3.250 0.1465 0.01278 0.00467 -0.1028 0.5895 0.0757
-3.000 0.1734 0.01270 0.00454 -0.1027 0.5867 0.0774
-2.750 0.1998 0.01255 0.00435 -0.1025 0.5838 0.0798
-2.500 0.2261 0.01236 0.00420 -0.1022 0.5820 0.0825
-2.250 0.2529 0.01223 0.00409 -0.1020 0.5799 0.0857
-2.000 0.2796 0.01209 0.00397 -0.1019 0.5777 0.0902
-1.750 0.3065 0.01197 0.00388 -0.1017 0.5755 0.0973
-1.500 0.3330 0.01182 0.00383 -0.1015 0.5734 0.1140
-1.250 0.3595 0.01167 0.00380 -0.1014 0.5712 0.1471
-1.000 0.3864 0.01158 0.00377 -0.1013 0.5690 0.1737
-0.750 0.4134 0.01150 0.00379 -0.1013 0.5667 0.2097
-0.500 0.4397 0.01134 0.00386 -0.1012 0.5648 0.2787
-0.250 0.4641 0.01102 0.00385 -0.1008 0.5634 0.3654
0.000 0.4850 0.01049 0.00393 -0.0997 0.5618 0.5489
0.250 0.5084 0.01025 0.00398 -0.0989 0.5601 0.6386
0.500 0.5293 0.00991 0.00408 -0.0973 0.5584 0.7561
0.750 0.5549 0.00976 0.00429 -0.0964 0.5568 0.8800
1.000 0.6000 0.00993 0.00452 -0.0997 0.5550 0.9383
1.250 0.6431 0.01013 0.00469 -0.1028 0.5532 0.9608
1.500 0.6928 0.01036 0.00486 -0.1074 0.5513 0.9748
1.750 0.7458 0.01060 0.00503 -0.1128 0.5494 0.9845
2.000 0.7905 0.01084 0.00521 -0.1166 0.5475 0.9894
2.250 0.8328 0.01095 0.00532 -0.1198 0.5462 0.9939
2.500 0.8799 0.01102 0.00539 -0.1242 0.5449 0.9981
2.750 0.9146 0.01109 0.00547 -0.1259 0.5433 1.0000
3.000 0.9375 0.01117 0.00556 -0.1251 0.5416 1.0000
3.250 0.9604 0.01125 0.00564 -0.1243 0.5397 1.0000
3.500 0.9829 0.01130 0.00568 -0.1234 0.5369 1.0000
3.750 1.0051 0.01132 0.00565 -0.1224 0.5332 1.0000
4.000 1.0284 0.01148 0.00575 -0.1216 0.5288 1.0000
4.250 1.0466 0.01144 0.00576 -0.1198 0.5251 1.0000
4.500 1.0663 0.01143 0.00578 -0.1182 0.5209 1.0000
4.750 1.0873 0.01146 0.00579 -0.1170 0.5174 1.0000
5.000 1.1095 0.01155 0.00585 -0.1159 0.5144 1.0000
5.250 1.1322 0.01170 0.00599 -0.1151 0.5109 1.0000
5.500 1.1499 0.01170 0.00606 -0.1131 0.5072 1.0000
5.750 1.1692 0.01174 0.00612 -0.1115 0.5032 1.0000
6.000 1.1889 0.01178 0.00617 -0.1099 0.4994 1.0000
6.250 1.2103 0.01190 0.00624 -0.1087 0.4951 1.0000
6.500 1.2265 0.01193 0.00635 -0.1065 0.4904 1.0000
6.750 1.2436 0.01197 0.00643 -0.1044 0.4853 1.0000
7.000 1.2606 0.01204 0.00649 -0.1023 0.4800 1.0000
7.250 1.2766 0.01212 0.00661 -0.1001 0.4737 1.0000
7.500 1.2903 0.01219 0.00670 -0.0974 0.4654 1.0000
7.750 1.3022 0.01230 0.00683 -0.0943 0.4564 1.0000
8.000 1.3135 0.01249 0.00699 -0.0913 0.4454 1.0000
8.250 1.3251 0.01275 0.00724 -0.0884 0.4289 1.0000
8.500 1.3313 0.01326 0.00765 -0.0848 0.3979 1.0000
8.750 1.3203 0.01462 0.00869 -0.0787 0.3428 1.0000
9.000 1.3075 0.01642 0.01020 -0.0730 0.2950 1.0000
9.250 1.2957 0.01840 0.01193 -0.0679 0.2513 1.0000
9.500 1.2813 0.02075 0.01403 -0.0630 0.2063 1.0000
9.750 1.2566 0.02403 0.01699 -0.0578 0.1470 1.0000
10.000 1.2327 0.02765 0.02038 -0.0534 0.1027 1.0000
10.250 1.2134 0.03127 0.02381 -0.0500 0.0631 1.0000
10.500 1.2113 0.03374 0.02625 -0.0483 0.0545 1.0000
10.750 1.2135 0.03595 0.02848 -0.0470 0.0510 1.0000
11.000 1.2180 0.03803 0.03061 -0.0460 0.0489 1.0000
11.250 1.2233 0.04009 0.03272 -0.0451 0.0474 1.0000
11.500 1.2272 0.04230 0.03499 -0.0442 0.0461 1.0000
11.750 1.2294 0.04471 0.03744 -0.0433 0.0450 1.0000
12.000 1.2297 0.04734 0.04012 -0.0424 0.0441 1.0000
12.250 1.2327 0.04974 0.04258 -0.0417 0.0434 1.0000
12.500 1.2374 0.05195 0.04486 -0.0410 0.0428 1.0000
12.750 1.2409 0.05431 0.04728 -0.0404 0.0422 1.0000
13.000 1.2442 0.05670 0.04972 -0.0398 0.0416 1.0000
13.250 1.2469 0.05919 0.05226 -0.0392 0.0410 1.0000
13.500 1.2491 0.06174 0.05486 -0.0387 0.0404 1.0000
13.750 1.2505 0.06439 0.05756 -0.0381 0.0398 1.0000
14.000 1.2506 0.06718 0.06040 -0.0376 0.0392 1.0000
14.250 1.2492 0.07018 0.06343 -0.0371 0.0387 1.0000
14.500 1.2469 0.07325 0.06655 -0.0365 0.0383 1.0000
14.750 1.2514 0.07564 0.06900 -0.0362 0.0380 1.0000
15.000 1.2565 0.07793 0.07134 -0.0360 0.0376 1.0000
15.250 1.2613 0.08028 0.07375 -0.0357 0.0373 1.0000
15.500 1.2657 0.08268 0.07621 -0.0355 0.0369 1.0000
15.750 1.2708 0.08499 0.07856 -0.0353 0.0365 1.0000
16.000 1.2764 0.08724 0.08086 -0.0351 0.0360 1.0000
16.250 1.2813 0.08958 0.08323 -0.0349 0.0355 1.0000
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