GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 420 AIRFOIL (goe420-il) Reynolds number: 200,000 Max Cl/Cd: 62.71 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe420-il-200000-n5.txt Download as CSV file: xf-goe420-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 420 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6140 0.07638 0.07120 -0.0917 1.0000 0.0377
-14.750 -0.6480 0.07020 0.06486 -0.0941 1.0000 0.0376
-14.500 -0.6508 0.06444 0.05895 -0.1000 0.9920 0.0378
-14.250 -0.6524 0.05952 0.05387 -0.1050 0.9840 0.0379
-14.000 -0.6494 0.05533 0.04953 -0.1096 0.9769 0.0381
-13.750 -0.6432 0.05159 0.04564 -0.1140 0.9698 0.0383
-13.500 -0.6329 0.04815 0.04206 -0.1184 0.9639 0.0386
-13.250 -0.6207 0.04504 0.03880 -0.1225 0.9572 0.0389
-13.000 -0.6042 0.04219 0.03580 -0.1267 0.9517 0.0392
-12.750 -0.5882 0.03967 0.03314 -0.1302 0.9444 0.0395
-12.500 -0.5694 0.03735 0.03068 -0.1337 0.9376 0.0400
-12.250 -0.5497 0.03527 0.02844 -0.1368 0.9311 0.0404
-12.000 -0.5328 0.03350 0.02653 -0.1388 0.9227 0.0408
-11.750 -0.5128 0.03178 0.02464 -0.1412 0.9158 0.0413
-11.500 -0.5002 0.03047 0.02325 -0.1414 0.9064 0.0417
-11.250 -0.4840 0.02924 0.02199 -0.1420 0.8988 0.0422
-11.000 -0.4744 0.02821 0.02091 -0.1412 0.8900 0.0427
-10.750 -0.4642 0.02724 0.01987 -0.1402 0.8820 0.0431
-10.500 -0.4545 0.02635 0.01891 -0.1388 0.8750 0.0436
-10.250 -0.4485 0.02560 0.01810 -0.1364 0.8667 0.0441
-10.000 -0.4389 0.02491 0.01732 -0.1344 0.8602 0.0447
-9.750 -0.4299 0.02429 0.01663 -0.1321 0.8530 0.0452
-9.500 -0.4179 0.02367 0.01592 -0.1302 0.8458 0.0458
-9.250 -0.4021 0.02303 0.01517 -0.1288 0.8403 0.0465
-9.000 -0.3896 0.02241 0.01454 -0.1269 0.8339 0.0471
-8.750 -0.3750 0.02184 0.01394 -0.1253 0.8275 0.0479
-8.500 -0.3574 0.02126 0.01331 -0.1240 0.8223 0.0489
-8.250 -0.3392 0.02075 0.01273 -0.1228 0.8171 0.0500
-8.000 -0.3218 0.02029 0.01222 -0.1214 0.8104 0.0513
-7.750 -0.3027 0.01976 0.01165 -0.1202 0.8046 0.0529
-7.500 -0.2809 0.01926 0.01107 -0.1195 0.8001 0.0547
-7.250 -0.2620 0.01887 0.01066 -0.1182 0.7936 0.0570
-7.000 -0.2415 0.01841 0.01017 -0.1171 0.7876 0.0595
-6.750 -0.2186 0.01795 0.00964 -0.1164 0.7825 0.0628
-6.500 -0.1977 0.01753 0.00920 -0.1154 0.7756 0.0668
-6.250 -0.1759 0.01713 0.00875 -0.1144 0.7682 0.0723
-6.000 -0.1520 0.01664 0.00823 -0.1138 0.7624 0.0804
-5.750 -0.1316 0.01619 0.00787 -0.1127 0.7545 0.0932
-5.500 -0.1087 0.01575 0.00752 -0.1120 0.7473 0.1161
-5.250 -0.0840 0.01542 0.00720 -0.1115 0.7408 0.1381
-5.000 -0.0607 0.01516 0.00695 -0.1107 0.7334 0.1541
-4.750 -0.0356 0.01488 0.00667 -0.1103 0.7276 0.1692
-4.500 -0.0105 0.01460 0.00642 -0.1098 0.7222 0.1867
-4.250 0.0133 0.01437 0.00628 -0.1091 0.7154 0.2079
-4.000 0.0386 0.01417 0.00614 -0.1087 0.7095 0.2349
-3.750 0.0651 0.01404 0.00602 -0.1084 0.7043 0.2617
-3.500 0.0899 0.01396 0.00600 -0.1078 0.6979 0.2847
-3.250 0.1161 0.01389 0.00592 -0.1074 0.6921 0.3033
-3.000 0.1437 0.01384 0.00579 -0.1072 0.6871 0.3190
-2.750 0.1684 0.01379 0.00578 -0.1066 0.6802 0.3317
-2.500 0.1948 0.01374 0.00569 -0.1062 0.6739 0.3416
-2.000 0.2478 0.01367 0.00552 -0.1054 0.6619 0.3581
-1.750 0.2738 0.01362 0.00547 -0.1050 0.6558 0.3659
-1.500 0.3012 0.01360 0.00538 -0.1048 0.6504 0.3748
-1.250 0.3266 0.01358 0.00537 -0.1042 0.6441 0.3825
-1.000 0.3523 0.01356 0.00534 -0.1037 0.6374 0.3909
-0.750 0.3795 0.01357 0.00526 -0.1034 0.6314 0.3998
-0.500 0.4040 0.01355 0.00530 -0.1028 0.6243 0.4096
-0.250 0.4296 0.01357 0.00528 -0.1022 0.6172 0.4203
0.000 0.4561 0.01356 0.00526 -0.1018 0.6113 0.4304
0.250 0.4804 0.01359 0.00531 -0.1011 0.6040 0.4410
0.500 0.5053 0.01359 0.00533 -0.1005 0.5970 0.4533
0.750 0.5307 0.01361 0.00534 -0.0999 0.5905 0.4663
1.000 0.5543 0.01364 0.00540 -0.0991 0.5825 0.4799
1.250 0.5788 0.01365 0.00542 -0.0983 0.5751 0.4933
1.500 0.6020 0.01368 0.00549 -0.0974 0.5668 0.5068
1.750 0.6255 0.01371 0.00554 -0.0965 0.5588 0.5218
2.000 0.6487 0.01374 0.00563 -0.0956 0.5514 0.5393
2.250 0.6709 0.01378 0.00573 -0.0944 0.5431 0.5599
2.750 0.7143 0.01387 0.00596 -0.0920 0.5268 0.6117
3.000 0.7360 0.01394 0.00605 -0.0907 0.5192 0.6411
3.250 0.7567 0.01401 0.00621 -0.0893 0.5114 0.6697
3.500 0.7770 0.01408 0.00632 -0.0878 0.5040 0.6995
3.750 0.7969 0.01413 0.00648 -0.0862 0.4970 0.7347
4.000 0.8153 0.01414 0.00670 -0.0841 0.4897 0.7933
4.250 0.8438 0.01425 0.00692 -0.0839 0.4823 0.9020
4.500 0.8893 0.01449 0.00716 -0.0878 0.4724 0.9764
4.750 0.9114 0.01475 0.00731 -0.0869 0.4654 1.0000
5.000 0.9285 0.01497 0.00751 -0.0850 0.4592 1.0000
5.250 0.9464 0.01521 0.00771 -0.0833 0.4535 1.0000
5.500 0.9654 0.01549 0.00791 -0.0818 0.4484 1.0000
5.750 0.9849 0.01576 0.00816 -0.0804 0.4439 1.0000
6.000 1.0040 0.01603 0.00842 -0.0790 0.4391 1.0000
6.250 1.0234 0.01632 0.00869 -0.0776 0.4345 1.0000
6.500 1.0435 0.01664 0.00895 -0.0764 0.4301 1.0000
6.750 1.0629 0.01695 0.00926 -0.0751 0.4256 1.0000
7.000 1.0810 0.01727 0.00961 -0.0737 0.4208 1.0000
7.250 1.0996 0.01762 0.00994 -0.0723 0.4161 1.0000
7.500 1.1195 0.01797 0.01026 -0.0712 0.4120 1.0000
7.750 1.1395 0.01833 0.01061 -0.0701 0.4081 1.0000
8.000 1.1564 0.01871 0.01105 -0.0686 0.4037 1.0000
8.250 1.1737 0.01911 0.01148 -0.0671 0.3990 1.0000
8.500 1.1917 0.01952 0.01187 -0.0658 0.3944 1.0000
8.750 1.2080 0.01997 0.01231 -0.0643 0.3890 1.0000
9.000 1.2185 0.02050 0.01291 -0.0620 0.3814 1.0000
9.250 1.2307 0.02105 0.01340 -0.0600 0.3738 1.0000
9.500 1.2407 0.02167 0.01409 -0.0579 0.3656 1.0000
9.750 1.2510 0.02233 0.01474 -0.0558 0.3578 1.0000
10.000 1.2626 0.02300 0.01545 -0.0540 0.3507 1.0000
10.250 1.2728 0.02375 0.01623 -0.0521 0.3426 1.0000
10.500 1.2828 0.02455 0.01703 -0.0503 0.3350 1.0000
10.750 1.2921 0.02542 0.01794 -0.0485 0.3262 1.0000
11.000 1.3005 0.02638 0.01890 -0.0467 0.3177 1.0000
11.250 1.3095 0.02736 0.01992 -0.0450 0.3092 1.0000
11.500 1.3179 0.02842 0.02098 -0.0434 0.3013 1.0000
11.750 1.3255 0.02957 0.02215 -0.0418 0.2928 1.0000
12.000 1.3323 0.03080 0.02340 -0.0402 0.2845 1.0000
12.250 1.3382 0.03216 0.02476 -0.0387 0.2758 1.0000
12.500 1.3435 0.03361 0.02623 -0.0372 0.2674 1.0000
12.750 1.3470 0.03525 0.02785 -0.0357 0.2585 1.0000
13.000 1.3516 0.03688 0.02951 -0.0344 0.2498 1.0000
13.250 1.3539 0.03874 0.03136 -0.0331 0.2417 1.0000
13.500 1.3577 0.04058 0.03323 -0.0320 0.2331 1.0000
13.750 1.3582 0.04273 0.03537 -0.0309 0.2249 1.0000
14.000 1.3619 0.04470 0.03738 -0.0300 0.2165 1.0000
14.250 1.3609 0.04713 0.03980 -0.0291 0.2086 1.0000
14.500 1.3635 0.04934 0.04207 -0.0284 0.1995 1.0000
14.750 1.3620 0.05197 0.04471 -0.0277 0.1907 1.0000
15.000 1.3598 0.05477 0.04754 -0.0272 0.1804 1.0000
15.250 1.3577 0.05764 0.05043 -0.0268 0.1702 1.0000
15.500 1.3524 0.06094 0.05373 -0.0265 0.1595 1.0000
15.750 1.3451 0.06454 0.05732 -0.0263 0.1492 1.0000
16.000 1.3373 0.06831 0.06109 -0.0263 0.1398 1.0000
16.250 1.3306 0.07204 0.06484 -0.0265 0.1321 1.0000
16.500 1.3220 0.07612 0.06891 -0.0268 0.1258 1.0000
16.750 1.3179 0.07969 0.07253 -0.0272 0.1202 1.0000
17.000 1.3113 0.08365 0.07650 -0.0277 0.1155 1.0000
17.250 1.3085 0.08717 0.08007 -0.0283 0.1114 1.0000
17.500 1.3056 0.09075 0.08369 -0.0289 0.1074 1.0000
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Polar data table (+)
Polar graphs
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