GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 200,000 Max Cl/Cd: 59.11 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe614-il-200000-n5.txt Download as CSV file: xf-goe614-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 614 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3776 0.06537 0.06060 -0.1195 0.9593 0.0329
-12.750 -0.4094 0.05561 0.05049 -0.1303 0.9508 0.0327
-12.500 -0.4170 0.04972 0.04436 -0.1377 0.9428 0.0327
-12.250 -0.4205 0.04526 0.03968 -0.1431 0.9328 0.0327
-12.000 -0.4102 0.04173 0.03600 -0.1484 0.9258 0.0329
-11.750 -0.4052 0.03906 0.03317 -0.1513 0.9149 0.0331
-11.500 -0.3892 0.03661 0.03053 -0.1546 0.9083 0.0333
-11.250 -0.3848 0.03502 0.02881 -0.1538 0.8965 0.0335
-11.000 -0.3631 0.03316 0.02678 -0.1557 0.8902 0.0339
-10.750 -0.3529 0.03187 0.02535 -0.1548 0.8791 0.0341
-10.250 -0.3150 0.02924 0.02241 -0.1551 0.8617 0.0345
-9.750 -0.2743 0.02708 0.01998 -0.1547 0.8440 0.0348
-9.250 -0.2331 0.02527 0.01792 -0.1538 0.8261 0.0353
-9.000 -0.2085 0.02441 0.01693 -0.1539 0.8180 0.0356
-8.750 -0.1918 0.02374 0.01618 -0.1523 0.8078 0.0357
-8.500 -0.1680 0.02302 0.01533 -0.1521 0.7995 0.0360
-8.250 -0.1507 0.02244 0.01468 -0.1505 0.7894 0.0362
-8.000 -0.1276 0.02184 0.01395 -0.1500 0.7809 0.0365
-7.750 -0.1095 0.02134 0.01338 -0.1484 0.7709 0.0368
-7.500 -0.0886 0.02066 0.01266 -0.1476 0.7622 0.0372
-7.250 -0.0716 0.02010 0.01209 -0.1459 0.7521 0.0377
-7.000 -0.0497 0.01958 0.01148 -0.1451 0.7430 0.0383
-6.750 -0.0314 0.01913 0.01099 -0.1435 0.7327 0.0388
-6.500 -0.0091 0.01871 0.01045 -0.1427 0.7239 0.0393
-6.250 0.0107 0.01832 0.01000 -0.1412 0.7136 0.0398
-6.000 0.0330 0.01797 0.00953 -0.1403 0.7042 0.0402
-5.750 0.0540 0.01765 0.00911 -0.1390 0.6936 0.0407
-5.500 0.0764 0.01735 0.00870 -0.1380 0.6840 0.0413
-5.250 0.0983 0.01708 0.00832 -0.1369 0.6739 0.0418
-5.000 0.1206 0.01677 0.00791 -0.1359 0.6648 0.0427
-4.750 0.1427 0.01650 0.00755 -0.1348 0.6550 0.0438
-4.500 0.1655 0.01629 0.00724 -0.1337 0.6456 0.0450
-4.250 0.1881 0.01610 0.00694 -0.1327 0.6358 0.0467
-4.000 0.2106 0.01587 0.00667 -0.1316 0.6270 0.0496
-3.750 0.2318 0.01550 0.00639 -0.1305 0.6181 0.0650
-3.500 0.2547 0.01531 0.00623 -0.1295 0.6103 0.1021
-3.250 0.2776 0.01518 0.00608 -0.1285 0.6019 0.1148
-3.000 0.3007 0.01504 0.00592 -0.1276 0.5944 0.1290
-2.750 0.3231 0.01491 0.00585 -0.1266 0.5863 0.1456
-2.500 0.3462 0.01484 0.00581 -0.1257 0.5787 0.1714
-2.250 0.3695 0.01481 0.00579 -0.1248 0.5717 0.1924
-2.000 0.3931 0.01482 0.00576 -0.1239 0.5647 0.2066
-1.500 0.4403 0.01485 0.00574 -0.1222 0.5524 0.2351
-1.250 0.4635 0.01487 0.00574 -0.1212 0.5460 0.2479
-0.750 0.5100 0.01493 0.00578 -0.1194 0.5344 0.2747
-0.500 0.5328 0.01496 0.00582 -0.1184 0.5287 0.2905
-0.250 0.5563 0.01501 0.00586 -0.1176 0.5238 0.3069
0.250 0.6023 0.01510 0.00600 -0.1157 0.5141 0.3390
0.500 0.6247 0.01515 0.00607 -0.1147 0.5091 0.3550
0.750 0.6473 0.01524 0.00612 -0.1137 0.5044 0.3721
1.000 0.6680 0.01528 0.00622 -0.1123 0.4991 0.3905
1.250 0.6883 0.01533 0.00632 -0.1108 0.4939 0.4117
1.500 0.7091 0.01540 0.00641 -0.1095 0.4891 0.4341
1.750 0.7301 0.01550 0.00650 -0.1082 0.4841 0.4586
2.000 0.7486 0.01555 0.00665 -0.1064 0.4786 0.4844
2.250 0.7673 0.01563 0.00679 -0.1047 0.4729 0.5111
2.500 0.7872 0.01574 0.00692 -0.1032 0.4681 0.5420
2.750 0.8059 0.01581 0.00710 -0.1015 0.4631 0.5763
3.000 0.8234 0.01587 0.00729 -0.0996 0.4572 0.6143
3.250 0.8409 0.01589 0.00747 -0.0976 0.4514 0.6747
3.750 0.9328 0.01606 0.00808 -0.1056 0.4378 1.0000
4.000 0.9512 0.01631 0.00824 -0.1040 0.4332 1.0000
4.250 0.9701 0.01656 0.00843 -0.1025 0.4290 1.0000
4.500 0.9892 0.01680 0.00866 -0.1011 0.4247 1.0000
4.750 1.0072 0.01707 0.00889 -0.0995 0.4198 1.0000
5.000 1.0253 0.01735 0.00912 -0.0980 0.4156 1.0000
5.250 1.0434 0.01766 0.00937 -0.0965 0.4113 1.0000
5.500 1.0611 0.01795 0.00968 -0.0949 0.4064 1.0000
5.750 1.0783 0.01827 0.00999 -0.0933 0.4016 1.0000
6.000 1.0956 0.01862 0.01029 -0.0918 0.3975 1.0000
6.250 1.1133 0.01898 0.01062 -0.0904 0.3936 1.0000
6.500 1.1308 0.01934 0.01101 -0.0890 0.3893 1.0000
6.750 1.1473 0.01973 0.01140 -0.0874 0.3847 1.0000
7.000 1.1631 0.02016 0.01181 -0.0858 0.3803 1.0000
7.250 1.1794 0.02060 0.01223 -0.0843 0.3763 1.0000
7.500 1.1957 0.02105 0.01272 -0.0829 0.3716 1.0000
7.750 1.2105 0.02155 0.01324 -0.0813 0.3668 1.0000
8.000 1.2246 0.02210 0.01376 -0.0796 0.3623 1.0000
8.250 1.2396 0.02265 0.01434 -0.0782 0.3578 1.0000
8.500 1.2533 0.02325 0.01497 -0.0766 0.3522 1.0000
8.750 1.2658 0.02393 0.01564 -0.0749 0.3471 1.0000
9.000 1.2790 0.02461 0.01634 -0.0734 0.3425 1.0000
9.250 1.2915 0.02535 0.01712 -0.0719 0.3366 1.0000
9.500 1.3030 0.02615 0.01793 -0.0703 0.3317 1.0000
9.750 1.3145 0.02699 0.01879 -0.0688 0.3270 1.0000
10.000 1.3263 0.02786 0.01970 -0.0674 0.3216 1.0000
10.250 1.3356 0.02887 0.02073 -0.0659 0.3158 1.0000
10.500 1.3444 0.02996 0.02183 -0.0643 0.3101 1.0000
10.750 1.3540 0.03105 0.02297 -0.0630 0.3044 1.0000
11.000 1.3619 0.03227 0.02420 -0.0615 0.2993 1.0000
11.250 1.3703 0.03352 0.02548 -0.0602 0.2944 1.0000
11.500 1.3791 0.03478 0.02679 -0.0590 0.2896 1.0000
11.750 1.3854 0.03624 0.02828 -0.0577 0.2846 1.0000
12.000 1.3917 0.03776 0.02982 -0.0565 0.2803 1.0000
12.250 1.4001 0.03917 0.03130 -0.0555 0.2763 1.0000
12.500 1.4052 0.04087 0.03304 -0.0544 0.2714 1.0000
12.750 1.4100 0.04263 0.03483 -0.0534 0.2674 1.0000
13.000 1.4162 0.04432 0.03658 -0.0525 0.2639 1.0000
13.250 1.4222 0.04609 0.03842 -0.0517 0.2601 1.0000
13.500 1.4271 0.04798 0.04038 -0.0509 0.2564 1.0000
13.750 1.4309 0.05000 0.04244 -0.0501 0.2528 1.0000
14.000 1.4337 0.05211 0.04458 -0.0494 0.2493 1.0000
14.250 1.4375 0.05426 0.04683 -0.0488 0.2451 1.0000
14.500 1.4382 0.05674 0.04937 -0.0482 0.2401 1.0000
14.750 1.4379 0.05933 0.05198 -0.0477 0.2356 1.0000
15.000 1.4372 0.06203 0.05474 -0.0473 0.2305 1.0000
15.250 1.4362 0.06483 0.05762 -0.0469 0.2253 1.0000
15.500 1.4326 0.06794 0.06076 -0.0466 0.2198 1.0000
15.750 1.4302 0.07098 0.06386 -0.0464 0.2146 1.0000
16.000 1.4294 0.07389 0.06686 -0.0463 0.2099 1.0000
16.250 1.4242 0.07731 0.07033 -0.0463 0.2043 1.0000
16.500 1.4224 0.08038 0.07347 -0.0463 0.2002 1.0000
16.750 1.4169 0.08402 0.07720 -0.0465 0.1928 1.0000
17.000 1.4100 0.08782 0.08104 -0.0467 0.1865 1.0000
17.250 1.4052 0.09144 0.08477 -0.0471 0.1791 1.0000
17.500 1.3980 0.09537 0.08876 -0.0475 0.1705 1.0000
17.750 1.3863 0.09996 0.09335 -0.0482 0.1564 1.0000
18.000 1.3700 0.10521 0.09857 -0.0490 0.1449 1.0000
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