GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 200,000 Max Cl/Cd: 70.06 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe621-il-200000-n5.txt Download as CSV file: xf-goe621-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 621 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4530 0.05872 0.05430 -0.1029 0.9725 0.0393
-11.500 -0.4949 0.04379 0.03884 -0.1250 0.9602 0.0391
-11.250 -0.5094 0.03913 0.03377 -0.1290 0.9481 0.0393
-11.000 -0.5007 0.03628 0.03066 -0.1308 0.9415 0.0395
-10.750 -0.4936 0.03460 0.02885 -0.1299 0.9318 0.0398
-10.500 -0.4761 0.03289 0.02699 -0.1304 0.9260 0.0401
-10.250 -0.4669 0.03156 0.02553 -0.1288 0.9162 0.0404
-10.000 -0.4490 0.03017 0.02397 -0.1286 0.9101 0.0408
-9.750 -0.4366 0.02900 0.02265 -0.1270 0.9008 0.0411
-9.500 -0.4181 0.02778 0.02126 -0.1264 0.8940 0.0416
-9.250 -0.4019 0.02675 0.02008 -0.1250 0.8852 0.0422
-9.000 -0.3826 0.02568 0.01881 -0.1242 0.8777 0.0429
-8.750 -0.3634 0.02469 0.01763 -0.1232 0.8700 0.0436
-8.500 -0.3432 0.02376 0.01650 -0.1222 0.8620 0.0442
-8.250 -0.3205 0.02285 0.01539 -0.1215 0.8554 0.0448
-8.000 -0.2999 0.02201 0.01449 -0.1205 0.8464 0.0453
-7.750 -0.2753 0.02121 0.01364 -0.1201 0.8401 0.0459
-7.500 -0.2539 0.02059 0.01298 -0.1190 0.8307 0.0465
-7.250 -0.2293 0.01994 0.01223 -0.1185 0.8240 0.0474
-7.000 -0.2063 0.01937 0.01159 -0.1177 0.8159 0.0482
-6.750 -0.1818 0.01881 0.01092 -0.1171 0.8087 0.0492
-6.500 -0.1571 0.01832 0.01030 -0.1165 0.8016 0.0505
-6.250 -0.1333 0.01778 0.00971 -0.1157 0.7938 0.0517
-6.000 -0.1079 0.01729 0.00916 -0.1153 0.7877 0.0531
-5.750 -0.0842 0.01689 0.00873 -0.1145 0.7802 0.0545
-5.500 -0.0588 0.01649 0.00825 -0.1140 0.7741 0.0562
-5.250 -0.0331 0.01614 0.00780 -0.1135 0.7685 0.0579
-5.000 -0.0091 0.01575 0.00741 -0.1128 0.7617 0.0602
-4.750 0.0169 0.01545 0.00703 -0.1124 0.7560 0.0631
-4.500 0.0428 0.01515 0.00670 -0.1119 0.7507 0.0670
-4.250 0.0679 0.01490 0.00645 -0.1113 0.7450 0.0722
-4.000 0.0940 0.01465 0.00620 -0.1109 0.7398 0.0792
-3.500 0.1464 0.01427 0.00581 -0.1101 0.7297 0.1011
-3.250 0.1724 0.01410 0.00564 -0.1096 0.7245 0.1140
-3.000 0.1995 0.01393 0.00545 -0.1094 0.7194 0.1272
-2.750 0.2251 0.01378 0.00532 -0.1088 0.7131 0.1411
-2.500 0.2505 0.01363 0.00520 -0.1083 0.7062 0.1572
-2.250 0.2774 0.01348 0.00506 -0.1080 0.7004 0.1784
-2.000 0.3025 0.01336 0.00501 -0.1073 0.6942 0.2033
-1.750 0.3279 0.01323 0.00498 -0.1068 0.6876 0.2332
-1.500 0.3546 0.01313 0.00493 -0.1064 0.6821 0.2674
-1.250 0.3795 0.01307 0.00494 -0.1057 0.6753 0.2951
-1.000 0.4049 0.01302 0.00492 -0.1051 0.6682 0.3183
-0.750 0.4316 0.01299 0.00487 -0.1047 0.6620 0.3383
-0.500 0.4562 0.01297 0.00489 -0.1039 0.6549 0.3558
-0.250 0.4823 0.01296 0.00487 -0.1034 0.6490 0.3725
0.000 0.5088 0.01295 0.00486 -0.1029 0.6436 0.3892
0.250 0.5334 0.01295 0.00490 -0.1022 0.6371 0.4063
0.500 0.5590 0.01293 0.00491 -0.1016 0.6312 0.4249
0.750 0.5847 0.01291 0.00492 -0.1010 0.6254 0.4460
1.000 0.6082 0.01287 0.00499 -0.1000 0.6180 0.4719
1.250 0.6328 0.01281 0.00499 -0.0992 0.6111 0.5031
1.500 0.6559 0.01273 0.00506 -0.0982 0.6039 0.5400
1.750 0.6780 0.01258 0.00510 -0.0969 0.5963 0.5933
2.000 0.7612 0.01198 0.00532 -0.1079 0.5852 0.9692
2.250 0.8019 0.01213 0.00536 -0.1106 0.5747 1.0000
2.500 0.8229 0.01225 0.00544 -0.1092 0.5642 1.0000
2.750 0.8439 0.01239 0.00550 -0.1077 0.5535 1.0000
3.000 0.8639 0.01253 0.00556 -0.1061 0.5406 1.0000
3.250 0.8831 0.01270 0.00565 -0.1043 0.5255 1.0000
3.500 0.9015 0.01288 0.00575 -0.1023 0.5088 1.0000
3.750 0.9185 0.01311 0.00586 -0.1001 0.4901 1.0000
4.000 0.9340 0.01338 0.00600 -0.0977 0.4690 1.0000
4.250 0.9480 0.01370 0.00618 -0.0950 0.4469 1.0000
4.500 0.9601 0.01408 0.00640 -0.0920 0.4253 1.0000
4.750 0.9718 0.01448 0.00666 -0.0890 0.4069 1.0000
5.000 0.9818 0.01489 0.00695 -0.0857 0.3906 1.0000
5.250 0.9927 0.01530 0.00726 -0.0826 0.3770 1.0000
5.500 1.0044 0.01574 0.00761 -0.0798 0.3652 1.0000
5.750 1.0166 0.01621 0.00798 -0.0771 0.3541 1.0000
6.000 1.0306 0.01665 0.00837 -0.0748 0.3438 1.0000
6.250 1.0429 0.01718 0.00880 -0.0723 0.3344 1.0000
6.500 1.0589 0.01761 0.00920 -0.0705 0.3257 1.0000
6.750 1.0729 0.01813 0.00966 -0.0684 0.3184 1.0000
7.000 1.0896 0.01857 0.01009 -0.0668 0.3121 1.0000
7.250 1.1055 0.01905 0.01056 -0.0650 0.3055 1.0000
7.500 1.1201 0.01961 0.01107 -0.0632 0.2999 1.0000
7.750 1.1376 0.02005 0.01154 -0.0618 0.2946 1.0000
8.000 1.1539 0.02056 0.01206 -0.0603 0.2891 1.0000
8.250 1.1689 0.02114 0.01261 -0.0586 0.2841 1.0000
8.500 1.1850 0.02169 0.01318 -0.0571 0.2793 1.0000
8.750 1.2013 0.02222 0.01375 -0.0557 0.2738 1.0000
9.000 1.2158 0.02285 0.01438 -0.0542 0.2684 1.0000
9.250 1.2297 0.02353 0.01505 -0.0526 0.2633 1.0000
9.500 1.2456 0.02412 0.01570 -0.0513 0.2577 1.0000
9.750 1.2590 0.02485 0.01644 -0.0497 0.2521 1.0000
10.000 1.2717 0.02564 0.01722 -0.0482 0.2473 1.0000
10.250 1.2870 0.02632 0.01798 -0.0470 0.2419 1.0000
10.500 1.3000 0.02713 0.01881 -0.0456 0.2365 1.0000
10.750 1.3106 0.02809 0.01977 -0.0440 0.2317 1.0000
11.000 1.3251 0.02887 0.02063 -0.0429 0.2263 1.0000
11.250 1.3367 0.02983 0.02162 -0.0415 0.2208 1.0000
11.500 1.3459 0.03096 0.02274 -0.0401 0.2160 1.0000
11.750 1.3591 0.03188 0.02375 -0.0390 0.2107 1.0000
12.000 1.3690 0.03302 0.02493 -0.0377 0.2052 1.0000
12.250 1.3770 0.03433 0.02623 -0.0364 0.2004 1.0000
12.500 1.3885 0.03544 0.02742 -0.0354 0.1950 1.0000
12.750 1.3970 0.03678 0.02880 -0.0342 0.1900 1.0000
13.000 1.4037 0.03829 0.03030 -0.0331 0.1859 1.0000
13.250 1.4145 0.03954 0.03165 -0.0322 0.1815 1.0000
13.500 1.4229 0.04099 0.03315 -0.0312 0.1771 1.0000
13.750 1.4285 0.04269 0.03486 -0.0302 0.1730 1.0000
14.000 1.4361 0.04426 0.03649 -0.0294 0.1691 1.0000
14.250 1.4439 0.04587 0.03818 -0.0286 0.1649 1.0000
14.500 1.4488 0.04775 0.04009 -0.0279 0.1608 1.0000
14.750 1.4524 0.04977 0.04211 -0.0271 0.1572 1.0000
15.000 1.4601 0.05148 0.04395 -0.0266 0.1535 1.0000
15.250 1.4650 0.05349 0.04602 -0.0260 0.1496 1.0000
15.500 1.4682 0.05568 0.04825 -0.0255 0.1464 1.0000
15.750 1.4708 0.05796 0.05054 -0.0251 0.1438 1.0000
16.000 1.4773 0.05992 0.05263 -0.0248 0.1411 1.0000
16.250 1.4816 0.06214 0.05496 -0.0245 0.1382 1.0000
16.500 1.4845 0.06453 0.05744 -0.0243 0.1354 1.0000
16.750 1.4850 0.06722 0.06018 -0.0242 0.1328 1.0000
17.000 1.4858 0.06992 0.06291 -0.0242 0.1302 1.0000
17.250 1.4887 0.07248 0.06562 -0.0243 0.1276 1.0000
17.500 1.4901 0.07524 0.06851 -0.0245 0.1252 1.0000
17.750 1.4894 0.07830 0.07166 -0.0248 0.1225 1.0000
18.000 1.4866 0.08168 0.07510 -0.0253 0.1199 1.0000
18.250 1.4841 0.08505 0.07852 -0.0258 0.1175 1.0000
18.500 1.4830 0.08836 0.08200 -0.0265 0.1151 1.0000
18.750 1.4801 0.09197 0.08575 -0.0273 0.1124 1.0000
19.000 1.4749 0.09594 0.08982 -0.0284 0.1097 1.0000
19.250 1.4676 0.10025 0.09418 -0.0297 0.1070 1.0000
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