GOE 404 AIRFOIL (goe404-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 404 AIRFOIL (goe404-il) Reynolds number: 200,000 Max Cl/Cd: 69.66 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe404-il-200000-n5.txt Download as CSV file: xf-goe404-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 404 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2853 0.12476 0.12081 -0.0288 1.0000 0.0486
-11.000 -0.2842 0.12129 0.11736 -0.0309 1.0000 0.0487
-10.750 -0.2804 0.11792 0.11402 -0.0325 1.0000 0.0487
-9.750 -0.2658 0.10208 0.09824 -0.0367 1.0000 0.0391
-9.500 -0.2632 0.09905 0.09527 -0.0375 1.0000 0.0390
-9.250 -0.2665 0.09565 0.09191 -0.0385 1.0000 0.0391
-9.000 -0.2584 0.09131 0.08758 -0.0425 0.9903 0.0391
-8.750 -0.2439 0.08716 0.08343 -0.0468 0.9761 0.0389
-8.500 -0.2308 0.08299 0.07925 -0.0510 0.9598 0.0387
-7.500 -0.3108 0.02587 0.01967 -0.0945 0.8792 0.0394
-7.250 -0.2879 0.02476 0.01841 -0.0939 0.8624 0.0397
-7.000 -0.2647 0.02375 0.01725 -0.0933 0.8454 0.0401
-6.750 -0.2411 0.02272 0.01602 -0.0927 0.8285 0.0406
-6.500 -0.2171 0.02168 0.01477 -0.0921 0.8115 0.0412
-6.250 -0.1927 0.02067 0.01351 -0.0915 0.7944 0.0418
-6.000 -0.1680 0.01971 0.01228 -0.0909 0.7779 0.0426
-5.750 -0.1427 0.01882 0.01111 -0.0903 0.7626 0.0435
-5.500 -0.1169 0.01829 0.01043 -0.0897 0.7482 0.0444
-5.250 -0.0906 0.01795 0.01000 -0.0892 0.7343 0.0454
-5.000 -0.0642 0.01753 0.00945 -0.0887 0.7217 0.0467
-4.750 -0.0378 0.01702 0.00875 -0.0882 0.7100 0.0481
-4.500 -0.0111 0.01662 0.00825 -0.0878 0.6985 0.0494
-4.250 0.0158 0.01637 0.00793 -0.0874 0.6880 0.0509
-4.000 0.0428 0.01604 0.00749 -0.0870 0.6769 0.0530
-3.750 0.0699 0.01579 0.00718 -0.0866 0.6663 0.0552
-3.500 0.0971 0.01562 0.00693 -0.0862 0.6555 0.0583
-3.250 0.1245 0.01550 0.00676 -0.0858 0.6453 0.0620
-3.000 0.1519 0.01536 0.00653 -0.0854 0.6349 0.0668
-2.750 0.1794 0.01532 0.00644 -0.0851 0.6241 0.0713
-2.250 0.2341 0.01519 0.00613 -0.0843 0.6010 0.0802
-2.000 0.2613 0.01515 0.00603 -0.0840 0.5894 0.0840
-1.750 0.2885 0.01512 0.00593 -0.0836 0.5773 0.0884
-1.500 0.3157 0.01502 0.00577 -0.0832 0.5651 0.0922
-1.250 0.3426 0.01501 0.00572 -0.0829 0.5527 0.0966
-1.000 0.3696 0.01502 0.00562 -0.0825 0.5391 0.1019
-0.750 0.3963 0.01494 0.00555 -0.0821 0.5253 0.1063
-0.500 0.4229 0.01488 0.00542 -0.0816 0.5118 0.1100
-0.250 0.4494 0.01483 0.00526 -0.0812 0.4991 0.1126
0.000 0.4758 0.01470 0.00510 -0.0807 0.4872 0.1148
0.250 0.5022 0.01463 0.00501 -0.0803 0.4768 0.1177
0.500 0.5285 0.01462 0.00495 -0.0798 0.4671 0.1209
0.750 0.5551 0.01462 0.00491 -0.0794 0.4585 0.1239
1.000 0.5816 0.01465 0.00487 -0.0790 0.4502 0.1268
1.250 0.6079 0.01465 0.00487 -0.0786 0.4429 0.1311
1.500 0.6345 0.01468 0.00490 -0.0783 0.4350 0.1365
2.000 0.6874 0.01481 0.00501 -0.0775 0.4206 0.1512
2.250 0.7136 0.01488 0.00509 -0.0771 0.4135 0.1656
2.500 0.7397 0.01494 0.00519 -0.0767 0.4073 0.1971
2.750 0.7589 0.01376 0.00542 -0.0754 0.4015 0.6917
3.250 0.8302 0.01373 0.00570 -0.0779 0.3905 1.0000
3.750 0.8820 0.01411 0.00601 -0.0770 0.3798 1.0000
4.000 0.9071 0.01436 0.00616 -0.0764 0.3743 1.0000
4.250 0.9325 0.01459 0.00634 -0.0759 0.3696 1.0000
4.500 0.9584 0.01480 0.00655 -0.0754 0.3651 1.0000
4.750 0.9839 0.01503 0.00675 -0.0749 0.3608 1.0000
5.000 1.0089 0.01528 0.00695 -0.0744 0.3565 1.0000
5.250 1.0338 0.01554 0.00717 -0.0738 0.3514 1.0000
5.500 1.0589 0.01575 0.00740 -0.0733 0.3454 1.0000
5.750 1.0835 0.01600 0.00763 -0.0727 0.3402 1.0000
6.000 1.1074 0.01630 0.00787 -0.0720 0.3353 1.0000
6.250 1.1325 0.01652 0.00814 -0.0715 0.3304 1.0000
6.500 1.1568 0.01678 0.00842 -0.0709 0.3251 1.0000
6.750 1.1801 0.01708 0.00869 -0.0702 0.3196 1.0000
7.000 1.2038 0.01735 0.00898 -0.0695 0.3136 1.0000
7.250 1.2268 0.01763 0.00928 -0.0687 0.3064 1.0000
7.500 1.2486 0.01796 0.00959 -0.0678 0.2994 1.0000
7.750 1.2713 0.01825 0.00993 -0.0670 0.2911 1.0000
8.000 1.2919 0.01862 0.01027 -0.0659 0.2830 1.0000
8.250 1.3130 0.01897 0.01065 -0.0650 0.2727 1.0000
8.500 1.3325 0.01938 0.01106 -0.0638 0.2616 1.0000
8.750 1.3505 0.01985 0.01150 -0.0624 0.2490 1.0000
9.000 1.3668 0.02039 0.01200 -0.0608 0.2352 1.0000
9.250 1.3802 0.02100 0.01257 -0.0588 0.2212 1.0000
9.500 1.3918 0.02174 0.01325 -0.0567 0.2082 1.0000
9.750 1.4029 0.02256 0.01403 -0.0546 0.1972 1.0000
10.000 1.4137 0.02345 0.01489 -0.0526 0.1894 1.0000
10.250 1.4236 0.02444 0.01587 -0.0507 0.1830 1.0000
10.500 1.4337 0.02545 0.01690 -0.0490 0.1782 1.0000
10.750 1.4441 0.02650 0.01798 -0.0474 0.1736 1.0000
11.000 1.4523 0.02774 0.01923 -0.0458 0.1696 1.0000
11.250 1.4591 0.02913 0.02064 -0.0442 0.1661 1.0000
11.500 1.4698 0.03030 0.02189 -0.0430 0.1630 1.0000
11.750 1.4788 0.03165 0.02330 -0.0418 0.1600 1.0000
12.000 1.4863 0.03317 0.02487 -0.0407 0.1573 1.0000
12.250 1.4922 0.03488 0.02663 -0.0397 0.1549 1.0000
12.500 1.4961 0.03681 0.02859 -0.0387 0.1525 1.0000
12.750 1.5046 0.03842 0.03030 -0.0380 0.1500 1.0000
13.000 1.5122 0.04014 0.03212 -0.0374 0.1472 1.0000
13.250 1.5177 0.04210 0.03417 -0.0369 0.1445 1.0000
13.500 1.5212 0.04430 0.03643 -0.0363 0.1419 1.0000
13.750 1.5226 0.04671 0.03888 -0.0359 0.1395 1.0000
14.000 1.5254 0.04903 0.04127 -0.0355 0.1373 1.0000
14.250 1.5307 0.05118 0.04356 -0.0353 0.1348 1.0000
14.500 1.5339 0.05358 0.04607 -0.0351 0.1321 1.0000
14.750 1.5350 0.05627 0.04885 -0.0351 0.1294 1.0000
15.000 1.5339 0.05923 0.05188 -0.0351 0.1269 1.0000
15.250 1.5328 0.06227 0.05497 -0.0353 0.1246 1.0000
15.500 1.5349 0.06502 0.05787 -0.0355 0.1218 1.0000
15.750 1.5343 0.06815 0.06112 -0.0358 0.1187 1.0000
16.000 1.5311 0.07167 0.06472 -0.0364 0.1158 1.0000
16.250 1.5258 0.07551 0.06861 -0.0371 0.1132 1.0000
16.500 1.5252 0.07880 0.07205 -0.0377 0.1099 1.0000
16.750 1.5213 0.08260 0.07595 -0.0385 0.1064 1.0000
17.000 1.5144 0.08687 0.08029 -0.0396 0.1033 1.0000
17.250 1.5096 0.09088 0.08440 -0.0406 0.1001 1.0000
17.500 1.5042 0.09500 0.08861 -0.0417 0.0965 1.0000
17.750 1.4963 0.09952 0.09319 -0.0431 0.0935 1.0000
18.000 1.4903 0.10376 0.09752 -0.0443 0.0906 1.0000
18.250 1.4844 0.10805 0.10190 -0.0457 0.0877 1.0000
18.500 1.4774 0.11254 0.10644 -0.0472 0.0852 1.0000
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