GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 200,000 Max Cl/Cd: 79.19 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe723-il-200000-n5.txt Download as CSV file: xf-goe723-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 723 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3362 0.10565 0.10179 -0.0459 1.0000 0.0461
-10.000 -0.3379 0.10177 0.09796 -0.0467 1.0000 0.0464
-9.750 -0.3272 0.09986 0.09607 -0.0449 1.0000 0.0470
-9.500 -0.3188 0.09814 0.09439 -0.0436 1.0000 0.0478
-9.000 -0.3524 0.08590 0.08226 -0.0480 1.0000 0.0393
-8.750 -0.3272 0.08402 0.08035 -0.0497 0.9957 0.0381
-8.500 -0.3139 0.07970 0.07603 -0.0540 0.9860 0.0373
-8.250 -0.3065 0.07469 0.07104 -0.0590 0.9705 0.0367
-8.000 -0.3026 0.06842 0.06476 -0.0661 0.9503 0.0369
-7.750 -0.3189 0.03970 0.03519 -0.1040 0.9201 0.0344
-7.500 -0.2979 0.03402 0.02888 -0.1098 0.9069 0.0343
-7.250 -0.2716 0.03067 0.02507 -0.1129 0.8952 0.0343
-7.000 -0.2442 0.02816 0.02215 -0.1149 0.8835 0.0345
-6.750 -0.2188 0.02629 0.01996 -0.1157 0.8703 0.0347
-6.500 -0.1930 0.02490 0.01829 -0.1162 0.8579 0.0354
-6.250 -0.1673 0.02361 0.01672 -0.1164 0.8463 0.0360
-6.000 -0.1428 0.02238 0.01520 -0.1162 0.8342 0.0364
-5.750 -0.1187 0.02126 0.01381 -0.1157 0.8226 0.0365
-5.500 -0.0936 0.02028 0.01258 -0.1153 0.8122 0.0367
-5.250 -0.0689 0.01942 0.01151 -0.1148 0.8017 0.0370
-5.000 -0.0438 0.01865 0.01057 -0.1142 0.7918 0.0373
-4.750 -0.0183 0.01796 0.00970 -0.1137 0.7825 0.0376
-4.500 0.0068 0.01735 0.00897 -0.1131 0.7732 0.0379
-4.250 0.0326 0.01682 0.00830 -0.1126 0.7651 0.0383
-4.000 0.0578 0.01635 0.00774 -0.1120 0.7564 0.0387
-3.750 0.0831 0.01580 0.00712 -0.1114 0.7487 0.0395
-3.500 0.1076 0.01529 0.00661 -0.1108 0.7405 0.0405
-3.250 0.1329 0.01489 0.00618 -0.1102 0.7333 0.0413
-3.000 0.1582 0.01454 0.00580 -0.1096 0.7262 0.0419
-2.750 0.1835 0.01424 0.00544 -0.1090 0.7188 0.0425
-2.500 0.2093 0.01398 0.00511 -0.1085 0.7123 0.0433
-2.250 0.2348 0.01374 0.00483 -0.1079 0.7051 0.0442
-2.000 0.2611 0.01357 0.00456 -0.1074 0.6989 0.0452
-1.750 0.2872 0.01340 0.00434 -0.1069 0.6923 0.0464
-1.500 0.3131 0.01320 0.00410 -0.1064 0.6855 0.0485
-1.250 0.3397 0.01308 0.00390 -0.1060 0.6800 0.0520
-1.000 0.3656 0.01292 0.00376 -0.1055 0.6730 0.0573
-0.750 0.3915 0.01268 0.00360 -0.1050 0.6667 0.0801
-0.500 0.4153 0.01209 0.00356 -0.1044 0.6607 0.2400
-0.250 0.4405 0.01191 0.00361 -0.1039 0.6535 0.3117
0.250 0.4914 0.01178 0.00368 -0.1026 0.6380 0.4039
0.500 0.5170 0.01175 0.00369 -0.1020 0.6310 0.4411
0.750 0.5423 0.01170 0.00376 -0.1013 0.6238 0.4768
1.000 0.5674 0.01165 0.00383 -0.1006 0.6172 0.5217
1.250 0.5928 0.01159 0.00388 -0.1000 0.6113 0.5683
1.500 0.6179 0.01152 0.00395 -0.0992 0.6044 0.6091
1.750 0.6441 0.01141 0.00398 -0.0987 0.5984 0.6657
2.250 0.7493 0.01107 0.00412 -0.1092 0.5835 1.0000
2.500 0.7751 0.01121 0.00421 -0.1087 0.5771 1.0000
2.750 0.8007 0.01134 0.00432 -0.1081 0.5698 1.0000
3.000 0.8261 0.01149 0.00440 -0.1075 0.5625 1.0000
3.250 0.8509 0.01163 0.00451 -0.1067 0.5529 1.0000
3.500 0.8752 0.01177 0.00462 -0.1059 0.5421 1.0000
3.750 0.8991 0.01193 0.00471 -0.1049 0.5299 1.0000
4.000 0.9225 0.01209 0.00482 -0.1039 0.5164 1.0000
4.250 0.9464 0.01226 0.00499 -0.1030 0.5045 1.0000
4.500 0.9701 0.01245 0.00515 -0.1021 0.4932 1.0000
4.750 0.9934 0.01266 0.00532 -0.1011 0.4812 1.0000
5.000 1.0163 0.01287 0.00552 -0.1001 0.4677 1.0000
5.250 1.0382 0.01311 0.00572 -0.0988 0.4510 1.0000
5.500 1.0590 0.01339 0.00593 -0.0974 0.4296 1.0000
5.750 1.0794 0.01370 0.00619 -0.0960 0.4088 1.0000
6.000 1.0989 0.01406 0.00647 -0.0944 0.3884 1.0000
6.250 1.1177 0.01446 0.00679 -0.0927 0.3667 1.0000
6.500 1.1353 0.01492 0.00716 -0.0908 0.3441 1.0000
6.750 1.1512 0.01546 0.00760 -0.0887 0.3191 1.0000
7.000 1.1652 0.01609 0.00809 -0.0863 0.2905 1.0000
7.250 1.1770 0.01683 0.00866 -0.0836 0.2521 1.0000
7.500 1.1736 0.01831 0.00963 -0.0788 0.1658 1.0000
7.750 1.1691 0.01978 0.01073 -0.0737 0.1173 1.0000
8.000 1.1760 0.02071 0.01160 -0.0705 0.1010 1.0000
8.250 1.1865 0.02148 0.01238 -0.0679 0.0900 1.0000
8.500 1.1965 0.02231 0.01321 -0.0654 0.0823 1.0000
8.750 1.2067 0.02316 0.01407 -0.0630 0.0769 1.0000
9.000 1.2159 0.02409 0.01503 -0.0607 0.0733 1.0000
9.250 1.2257 0.02504 0.01604 -0.0586 0.0703 1.0000
9.500 1.2343 0.02611 0.01716 -0.0565 0.0678 1.0000
9.750 1.2413 0.02734 0.01842 -0.0544 0.0658 1.0000
10.000 1.2463 0.02878 0.01991 -0.0524 0.0641 1.0000
10.250 1.2529 0.03019 0.02139 -0.0506 0.0627 1.0000
10.500 1.2603 0.03161 0.02291 -0.0491 0.0614 1.0000
10.750 1.2674 0.03311 0.02449 -0.0477 0.0599 1.0000
11.000 1.2736 0.03473 0.02619 -0.0463 0.0584 1.0000
11.250 1.2792 0.03646 0.02798 -0.0450 0.0570 1.0000
11.500 1.2832 0.03837 0.02993 -0.0438 0.0555 1.0000
11.750 1.2847 0.04055 0.03213 -0.0425 0.0540 1.0000
12.000 1.2914 0.04230 0.03398 -0.0416 0.0527 1.0000
12.250 1.2989 0.04401 0.03580 -0.0407 0.0513 1.0000
12.500 1.3057 0.04580 0.03768 -0.0399 0.0498 1.0000
12.750 1.3115 0.04771 0.03966 -0.0390 0.0484 1.0000
13.000 1.3167 0.04970 0.04172 -0.0383 0.0471 1.0000
13.250 1.3208 0.05181 0.04388 -0.0376 0.0460 1.0000
13.500 1.3239 0.05402 0.04608 -0.0367 0.0447 1.0000
13.750 1.3310 0.05596 0.04818 -0.0362 0.0435 1.0000
14.000 1.3371 0.05802 0.05037 -0.0358 0.0421 1.0000
14.250 1.3423 0.06019 0.05264 -0.0354 0.0408 1.0000
14.500 1.3467 0.06249 0.05502 -0.0351 0.0395 1.0000
14.750 1.3503 0.06492 0.05751 -0.0350 0.0384 1.0000
15.000 1.3530 0.06742 0.06003 -0.0347 0.0374 1.0000
15.250 1.3577 0.06985 0.06264 -0.0346 0.0362 1.0000
15.500 1.3612 0.07243 0.06536 -0.0346 0.0349 1.0000
15.750 1.3638 0.07517 0.06821 -0.0348 0.0336 1.0000
16.000 1.3659 0.07801 0.07114 -0.0351 0.0327 1.0000
16.250 1.3669 0.08105 0.07424 -0.0355 0.0319 1.0000
16.500 1.3683 0.08402 0.07731 -0.0358 0.0311 1.0000
16.750 1.3696 0.08708 0.08054 -0.0361 0.0299 1.0000
17.000 1.3698 0.09036 0.08396 -0.0368 0.0288 1.0000
17.250 1.3694 0.09381 0.08752 -0.0376 0.0279 1.0000
17.500 1.3687 0.09732 0.09111 -0.0386 0.0273 1.0000
17.750 1.3673 0.10100 0.09487 -0.0398 0.0267 1.0000
18.000 1.3653 0.10474 0.09874 -0.0407 0.0259 1.0000
18.250 1.3627 0.10865 0.10283 -0.0418 0.0251 1.0000
18.500 1.3594 0.11275 0.10709 -0.0432 0.0244 1.0000
18.750 1.3558 0.11698 0.11145 -0.0448 0.0238 1.0000
19.000 1.3521 0.12129 0.11587 -0.0467 0.0233 1.0000
19.250 1.3484 0.12568 0.12035 -0.0487 0.0228 1.0000
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