GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 500,000 Max Cl/Cd: 84.83 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe614-il-500000.txt Download as CSV file: xf-goe614-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.0549 0.11013 0.10765 -0.1005 0.9703 0.0464
-12.250 -0.4343 0.03671 0.03252 -0.1629 0.9437 0.0357
-12.000 -0.4186 0.03478 0.03033 -0.1653 0.9372 0.0354
-11.750 -0.4028 0.03359 0.02898 -0.1657 0.9277 0.0353
-11.500 -0.3819 0.03196 0.02716 -0.1669 0.9202 0.0352
-11.250 -0.3605 0.02929 0.02441 -0.1677 0.9115 0.0350
-11.000 -0.3410 0.02756 0.02252 -0.1681 0.9026 0.0349
-10.750 -0.3219 0.02606 0.02084 -0.1680 0.8926 0.0348
-10.500 -0.3055 0.02491 0.01955 -0.1670 0.8820 0.0348
-10.250 -0.2833 0.02381 0.01826 -0.1669 0.8729 0.0349
-10.000 -0.2681 0.02293 0.01726 -0.1652 0.8619 0.0349
-9.750 -0.2468 0.02210 0.01626 -0.1646 0.8532 0.0350
-9.500 -0.2288 0.02134 0.01539 -0.1632 0.8428 0.0351
-9.250 -0.2085 0.02076 0.01466 -0.1622 0.8337 0.0353
-9.000 -0.1889 0.01956 0.01340 -0.1611 0.8243 0.0355
-8.750 -0.1675 0.01863 0.01242 -0.1603 0.8159 0.0358
-8.500 -0.1478 0.01798 0.01173 -0.1590 0.8063 0.0359
-8.250 -0.1267 0.01738 0.01105 -0.1579 0.7975 0.0361
-8.000 -0.1073 0.01682 0.01045 -0.1565 0.7878 0.0364
-7.750 -0.0862 0.01632 0.00989 -0.1554 0.7792 0.0366
-7.500 -0.0664 0.01585 0.00938 -0.1539 0.7697 0.0368
-7.250 -0.0453 0.01543 0.00888 -0.1527 0.7608 0.0371
-7.000 -0.0253 0.01502 0.00843 -0.1513 0.7508 0.0373
-6.750 -0.0043 0.01465 0.00799 -0.1500 0.7413 0.0376
-6.500 0.0162 0.01430 0.00757 -0.1486 0.7309 0.0380
-6.250 0.0373 0.01397 0.00719 -0.1473 0.7211 0.0384
-6.000 0.0585 0.01367 0.00682 -0.1459 0.7108 0.0387
-5.750 0.0799 0.01338 0.00646 -0.1446 0.7007 0.0392
-5.250 0.1233 0.01293 0.00586 -0.1421 0.6793 0.0402
-5.000 0.1438 0.01261 0.00546 -0.1407 0.6686 0.0409
-4.750 0.1651 0.01235 0.00513 -0.1393 0.6578 0.0418
-4.500 0.1874 0.01218 0.00489 -0.1382 0.6477 0.0427
-4.250 0.2097 0.01204 0.00466 -0.1369 0.6375 0.0437
-4.000 0.2326 0.01192 0.00447 -0.1358 0.6278 0.0449
-3.750 0.2549 0.01181 0.00427 -0.1346 0.6182 0.0468
-3.500 0.2776 0.01165 0.00409 -0.1335 0.6089 0.0502
-3.250 0.2977 0.01134 0.00391 -0.1320 0.5998 0.0911
-3.000 0.3205 0.01121 0.00383 -0.1310 0.5913 0.1106
-2.750 0.3427 0.01113 0.00373 -0.1298 0.5829 0.1264
-2.500 0.3648 0.01094 0.00368 -0.1287 0.5755 0.1610
-2.250 0.3875 0.01088 0.00369 -0.1277 0.5679 0.1931
-2.000 0.4107 0.01091 0.00370 -0.1267 0.5610 0.2114
-1.750 0.4345 0.01090 0.00370 -0.1258 0.5542 0.2247
-1.500 0.4574 0.01094 0.00370 -0.1247 0.5474 0.2365
-1.250 0.4806 0.01097 0.00372 -0.1237 0.5412 0.2472
-1.000 0.5034 0.01099 0.00373 -0.1226 0.5346 0.2583
-0.750 0.5248 0.01102 0.00374 -0.1213 0.5284 0.2697
-0.500 0.5471 0.01105 0.00377 -0.1201 0.5227 0.2815
-0.250 0.5684 0.01106 0.00380 -0.1187 0.5165 0.2945
0.000 0.5893 0.01110 0.00383 -0.1173 0.5105 0.3091
0.250 0.6112 0.01114 0.00389 -0.1161 0.5049 0.3245
0.500 0.6327 0.01114 0.00394 -0.1148 0.4995 0.3427
0.750 0.6534 0.01118 0.00401 -0.1134 0.4939 0.3659
1.000 0.6750 0.01127 0.00412 -0.1122 0.4886 0.3918
1.250 0.6962 0.01128 0.00421 -0.1108 0.4834 0.4153
1.500 0.7166 0.01134 0.00430 -0.1094 0.4776 0.4390
1.750 0.7367 0.01146 0.00442 -0.1079 0.4719 0.4648
2.000 0.7578 0.01149 0.00455 -0.1066 0.4674 0.4939
2.250 0.7778 0.01152 0.00467 -0.1051 0.4620 0.5250
2.500 0.7976 0.01160 0.00480 -0.1035 0.4574 0.5594
2.750 0.8175 0.01168 0.00496 -0.1020 0.4531 0.5988
3.000 0.8365 0.01162 0.00511 -0.1003 0.4497 0.6549
3.250 0.9299 0.01136 0.00555 -0.1144 0.4431 1.0000
3.500 0.9496 0.01154 0.00567 -0.1128 0.4392 1.0000
3.750 0.9699 0.01176 0.00582 -0.1115 0.4354 1.0000
4.000 0.9908 0.01189 0.00595 -0.1103 0.4318 1.0000
4.250 1.0114 0.01205 0.00609 -0.1090 0.4278 1.0000
4.500 1.0314 0.01225 0.00625 -0.1076 0.4238 1.0000
4.750 1.0506 0.01249 0.00643 -0.1062 0.4198 1.0000
5.000 1.0710 0.01269 0.00662 -0.1049 0.4159 1.0000
5.250 1.0918 0.01287 0.00681 -0.1038 0.4121 1.0000
5.500 1.1111 0.01310 0.00701 -0.1024 0.4074 1.0000
5.750 1.1298 0.01338 0.00724 -0.1009 0.4033 1.0000
6.000 1.1493 0.01363 0.00749 -0.0997 0.3993 1.0000
6.250 1.1698 0.01385 0.00773 -0.0986 0.3951 1.0000
6.500 1.1889 0.01412 0.00798 -0.0973 0.3905 1.0000
6.750 1.2056 0.01448 0.00829 -0.0957 0.3856 1.0000
7.000 1.2251 0.01477 0.00860 -0.0945 0.3813 1.0000
7.250 1.2447 0.01506 0.00890 -0.0934 0.3766 1.0000
7.500 1.2619 0.01543 0.00926 -0.0920 0.3716 1.0000
7.750 1.2782 0.01588 0.00966 -0.0904 0.3668 1.0000
8.000 1.2979 0.01619 0.01002 -0.0895 0.3621 1.0000
8.250 1.3151 0.01662 0.01045 -0.0882 0.3567 1.0000
8.500 1.3304 0.01714 0.01094 -0.0866 0.3516 1.0000
8.750 1.3485 0.01757 0.01140 -0.0855 0.3465 1.0000
9.000 1.3653 0.01806 0.01190 -0.0843 0.3408 1.0000
9.250 1.3786 0.01873 0.01254 -0.0827 0.3351 1.0000
9.500 1.3958 0.01925 0.01309 -0.0817 0.3293 1.0000
9.750 1.4105 0.01990 0.01375 -0.0803 0.3231 1.0000
10.000 1.4231 0.02069 0.01452 -0.0788 0.3169 1.0000
10.250 1.4383 0.02137 0.01522 -0.0777 0.3103 1.0000
10.500 1.4496 0.02228 0.01611 -0.0762 0.3041 1.0000
10.750 1.4625 0.02313 0.01699 -0.0749 0.2974 1.0000
11.000 1.4745 0.02407 0.01793 -0.0736 0.2913 1.0000
11.250 1.4838 0.02520 0.01905 -0.0722 0.2851 1.0000
11.500 1.4936 0.02635 0.02020 -0.0708 0.2768 1.0000
11.750 1.5002 0.02773 0.02157 -0.0693 0.2699 1.0000
12.000 1.5091 0.02900 0.02286 -0.0680 0.2628 1.0000
12.250 1.5134 0.03065 0.02449 -0.0665 0.2563 1.0000
12.500 1.5237 0.03190 0.02578 -0.0655 0.2508 1.0000
12.750 1.5286 0.03359 0.02748 -0.0642 0.2445 1.0000
13.000 1.5337 0.03530 0.02920 -0.0630 0.2399 1.0000
13.250 1.5419 0.03681 0.03075 -0.0621 0.2345 1.0000
13.500 1.5453 0.03876 0.03272 -0.0610 0.2293 1.0000
13.750 1.5486 0.04075 0.03473 -0.0600 0.2249 1.0000
14.000 1.5555 0.04246 0.03649 -0.0592 0.2199 1.0000
14.250 1.5562 0.04478 0.03884 -0.0582 0.2146 1.0000
14.500 1.5571 0.04712 0.04121 -0.0574 0.2095 1.0000
14.750 1.5611 0.04922 0.04336 -0.0567 0.2038 1.0000
15.000 1.5549 0.05235 0.04650 -0.0558 0.1971 1.0000
15.250 1.5592 0.05448 0.04869 -0.0553 0.1919 1.0000
15.500 1.5540 0.05762 0.05185 -0.0546 0.1842 1.0000
15.750 1.5509 0.06060 0.05486 -0.0541 0.1752 1.0000
16.000 1.5319 0.06535 0.05957 -0.0534 0.1567 1.0000
16.250 1.5056 0.07103 0.06518 -0.0528 0.1403 1.0000
16.500 1.4909 0.07551 0.06967 -0.0525 0.1335 1.0000
16.750 1.4793 0.07969 0.07388 -0.0523 0.1300 1.0000
17.000 1.4702 0.08361 0.07785 -0.0523 0.1273 1.0000
17.250 1.4612 0.08757 0.08185 -0.0523 0.1248 1.0000
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