GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 567 AIRFOIL (goe567-il) Reynolds number: 200,000 Max Cl/Cd: 79.79 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe567-il-200000-n5.txt Download as CSV file: xf-goe567-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 567 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6609 0.05024 0.04614 -0.0951 0.9918 0.0463
-12.000 -0.6825 0.03979 0.03525 -0.1111 0.9738 0.0472
-11.750 -0.6643 0.03553 0.03074 -0.1201 0.9619 0.0485
-11.500 -0.6313 0.03464 0.02982 -0.1238 0.9571 0.0499
-11.250 -0.6077 0.03329 0.02835 -0.1265 0.9467 0.0514
-11.000 -0.5831 0.03134 0.02610 -0.1301 0.9377 0.0535
-10.750 -0.5586 0.02912 0.02345 -0.1335 0.9283 0.0556
-10.500 -0.5303 0.02864 0.02300 -0.1345 0.9189 0.0571
-10.250 -0.4973 0.02812 0.02245 -0.1366 0.9114 0.0588
-10.000 -0.4707 0.02722 0.02137 -0.1378 0.9002 0.0607
-9.750 -0.4427 0.02595 0.01981 -0.1395 0.8902 0.0626
-9.500 -0.4147 0.02480 0.01832 -0.1408 0.8795 0.0642
-9.250 -0.3884 0.02372 0.01711 -0.1416 0.8681 0.0657
-9.000 -0.3603 0.02294 0.01624 -0.1423 0.8578 0.0669
-8.750 -0.3329 0.02223 0.01541 -0.1428 0.8471 0.0682
-8.500 -0.3067 0.02159 0.01462 -0.1430 0.8367 0.0698
-8.250 -0.2796 0.02095 0.01379 -0.1433 0.8276 0.0716
-8.000 -0.2540 0.02035 0.01299 -0.1433 0.8177 0.0733
-7.750 -0.2273 0.01978 0.01221 -0.1434 0.8096 0.0746
-7.500 -0.2018 0.01915 0.01144 -0.1433 0.8009 0.0759
-7.250 -0.1758 0.01848 0.01072 -0.1433 0.7937 0.0777
-7.000 -0.1502 0.01802 0.01021 -0.1431 0.7857 0.0795
-6.750 -0.1235 0.01761 0.00969 -0.1431 0.7789 0.0814
-6.500 -0.0973 0.01720 0.00920 -0.1429 0.7719 0.0832
-6.250 -0.0708 0.01682 0.00871 -0.1428 0.7652 0.0850
-6.000 -0.0437 0.01651 0.00825 -0.1427 0.7592 0.0869
-5.750 -0.0176 0.01611 0.00781 -0.1426 0.7525 0.0889
-5.500 0.0089 0.01570 0.00737 -0.1425 0.7464 0.0913
-5.250 0.0357 0.01539 0.00701 -0.1424 0.7407 0.0936
-5.000 0.0624 0.01512 0.00669 -0.1423 0.7343 0.0960
-4.750 0.0898 0.01490 0.00638 -0.1422 0.7287 0.0989
-4.500 0.1172 0.01470 0.00610 -0.1421 0.7232 0.1016
-4.250 0.1439 0.01440 0.00581 -0.1420 0.7169 0.1053
-4.000 0.1714 0.01419 0.00555 -0.1420 0.7114 0.1092
-3.750 0.1989 0.01402 0.00533 -0.1420 0.7060 0.1139
-3.500 0.2261 0.01381 0.00514 -0.1419 0.6998 0.1207
-3.250 0.2538 0.01364 0.00493 -0.1419 0.6943 0.1309
-3.000 0.2812 0.01343 0.00477 -0.1419 0.6888 0.1479
-2.750 0.3084 0.01322 0.00465 -0.1418 0.6826 0.1753
-2.500 0.3359 0.01304 0.00453 -0.1419 0.6772 0.2088
-2.250 0.3633 0.01290 0.00447 -0.1418 0.6715 0.2428
-2.000 0.3905 0.01280 0.00446 -0.1417 0.6652 0.2737
-1.750 0.4181 0.01275 0.00443 -0.1416 0.6598 0.2999
-1.500 0.4456 0.01273 0.00444 -0.1415 0.6540 0.3222
-1.250 0.4728 0.01272 0.00445 -0.1413 0.6477 0.3416
-1.000 0.5004 0.01273 0.00444 -0.1411 0.6422 0.3617
-0.750 0.5275 0.01275 0.00451 -0.1409 0.6361 0.3830
-0.500 0.5547 0.01278 0.00456 -0.1407 0.6300 0.4015
0.000 0.6088 0.01286 0.00463 -0.1402 0.6168 0.4317
0.250 0.6357 0.01291 0.00467 -0.1399 0.6102 0.4463
0.500 0.6623 0.01295 0.00474 -0.1395 0.6031 0.4609
0.750 0.6889 0.01301 0.00479 -0.1392 0.5959 0.4742
1.000 0.7155 0.01307 0.00484 -0.1388 0.5888 0.4871
1.250 0.7419 0.01313 0.00492 -0.1385 0.5818 0.4984
1.500 0.7686 0.01321 0.00497 -0.1382 0.5761 0.5089
1.750 0.7949 0.01329 0.00508 -0.1378 0.5694 0.5204
2.000 0.8210 0.01336 0.00516 -0.1374 0.5625 0.5313
2.250 0.8470 0.01345 0.00526 -0.1370 0.5557 0.5423
2.500 0.8729 0.01354 0.00537 -0.1366 0.5489 0.5541
2.750 0.8990 0.01364 0.00548 -0.1362 0.5436 0.5657
3.000 0.9248 0.01374 0.00564 -0.1358 0.5376 0.5777
3.250 0.9505 0.01384 0.00578 -0.1353 0.5316 0.5905
3.750 1.0014 0.01406 0.00611 -0.1344 0.5204 0.6196
4.000 1.0258 0.01417 0.00626 -0.1337 0.5130 0.6367
4.250 1.0493 0.01426 0.00643 -0.1328 0.5049 0.6569
4.500 1.0725 0.01435 0.00659 -0.1319 0.4960 0.6839
4.750 1.0949 0.01437 0.00677 -0.1308 0.4875 0.7306
5.000 1.1181 0.01418 0.00689 -0.1296 0.4795 1.0000
5.250 1.1416 0.01441 0.00711 -0.1289 0.4710 1.0000
5.500 1.1643 0.01466 0.00732 -0.1280 0.4622 1.0000
5.750 1.1872 0.01490 0.00757 -0.1271 0.4534 1.0000
6.000 1.2090 0.01517 0.00780 -0.1261 0.4450 1.0000
6.250 1.2311 0.01543 0.00809 -0.1251 0.4363 1.0000
6.500 1.2516 0.01573 0.00837 -0.1239 0.4276 1.0000
6.750 1.2724 0.01602 0.00868 -0.1227 0.4178 1.0000
7.000 1.2916 0.01634 0.00901 -0.1212 0.4082 1.0000
7.250 1.3088 0.01669 0.00935 -0.1194 0.3969 1.0000
7.500 1.3254 0.01704 0.00971 -0.1175 0.3859 1.0000
7.750 1.3403 0.01745 0.01011 -0.1153 0.3745 1.0000
8.000 1.3529 0.01793 0.01058 -0.1129 0.3603 1.0000
8.250 1.3649 0.01848 0.01110 -0.1104 0.3458 1.0000
8.500 1.3754 0.01911 0.01170 -0.1078 0.3295 1.0000
8.750 1.3846 0.01983 0.01239 -0.1051 0.3123 1.0000
9.000 1.3896 0.02078 0.01325 -0.1020 0.2908 1.0000
9.250 1.3916 0.02195 0.01433 -0.0988 0.2681 1.0000
9.500 1.3941 0.02321 0.01552 -0.0958 0.2470 1.0000
9.750 1.3961 0.02461 0.01686 -0.0930 0.2278 1.0000
10.000 1.3961 0.02625 0.01842 -0.0903 0.2080 1.0000
10.250 1.3961 0.02802 0.02013 -0.0879 0.1869 1.0000
10.500 1.3945 0.03002 0.02205 -0.0856 0.1652 1.0000
10.750 1.3920 0.03222 0.02418 -0.0834 0.1474 1.0000
11.000 1.3904 0.03446 0.02638 -0.0816 0.1357 1.0000
11.250 1.3925 0.03651 0.02844 -0.0801 0.1286 1.0000
11.500 1.3930 0.03875 0.03070 -0.0787 0.1226 1.0000
11.750 1.3971 0.04076 0.03277 -0.0776 0.1172 1.0000
12.000 1.3992 0.04300 0.03506 -0.0765 0.1122 1.0000
12.250 1.3993 0.04552 0.03761 -0.0755 0.1077 1.0000
12.500 1.4060 0.04745 0.03964 -0.0748 0.1024 1.0000
12.750 1.4086 0.04985 0.04210 -0.0741 0.0970 1.0000
13.000 1.4123 0.05219 0.04451 -0.0735 0.0921 1.0000
13.250 1.4188 0.05429 0.04671 -0.0730 0.0851 1.0000
13.500 1.4221 0.05679 0.04925 -0.0726 0.0755 1.0000
13.750 1.4220 0.05974 0.05218 -0.0723 0.0696 1.0000
14.000 1.4216 0.06281 0.05523 -0.0721 0.0655 1.0000
14.250 1.4217 0.06590 0.05835 -0.0720 0.0629 1.0000
14.500 1.4221 0.06901 0.06154 -0.0720 0.0608 1.0000
14.750 1.4223 0.07221 0.06480 -0.0720 0.0592 1.0000
15.000 1.4212 0.07563 0.06828 -0.0722 0.0574 1.0000
15.250 1.4193 0.07922 0.07192 -0.0725 0.0556 1.0000
15.500 1.4217 0.08227 0.07509 -0.0728 0.0538 1.0000
15.750 1.4228 0.08552 0.07845 -0.0732 0.0518 1.0000
16.000 1.4225 0.08904 0.08205 -0.0737 0.0502 1.0000
16.250 1.4202 0.09286 0.08594 -0.0744 0.0486 1.0000
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Polar data table (+)
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