GOE 404 AIRFOIL (goe404-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 404 AIRFOIL (goe404-il) Reynolds number: 500,000 Max Cl/Cd: 98.85 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe404-il-500000.txt Download as CSV file: xf-goe404-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1762 0.11007 0.10784 -0.0360 1.0000 0.0398
-10.500 -0.1739 0.10753 0.10532 -0.0361 0.9995 0.0405
-10.250 -0.1945 0.09986 0.09764 -0.0434 0.9962 0.0428
-10.000 -0.1731 0.09664 0.09442 -0.0445 0.9917 0.0430
-9.750 -0.1554 0.09359 0.09138 -0.0459 0.9848 0.0433
-9.500 -0.1407 0.09043 0.08821 -0.0477 0.9762 0.0437
-9.250 -0.1286 0.08717 0.08495 -0.0495 0.9654 0.0442
-9.000 -0.1210 0.08395 0.08171 -0.0507 0.9509 0.0450
-8.750 -0.1193 0.08058 0.07831 -0.0514 0.9337 0.0463
-8.500 -0.4000 0.02626 0.02223 -0.0977 0.9391 0.0375
-8.250 -0.3876 0.02293 0.01837 -0.0969 0.9255 0.0377
-8.000 -0.3685 0.02113 0.01621 -0.0959 0.9132 0.0379
-7.750 -0.3470 0.01988 0.01467 -0.0949 0.9007 0.0381
-7.500 -0.3260 0.01828 0.01284 -0.0940 0.8867 0.0385
-7.250 -0.3024 0.01732 0.01177 -0.0932 0.8724 0.0389
-7.000 -0.2776 0.01670 0.01105 -0.0925 0.8568 0.0394
-6.750 -0.2524 0.01615 0.01039 -0.0918 0.8392 0.0400
-6.500 -0.2270 0.01556 0.00964 -0.0911 0.8198 0.0406
-6.250 -0.2014 0.01498 0.00888 -0.0904 0.7998 0.0411
-6.000 -0.1756 0.01446 0.00818 -0.0898 0.7805 0.0417
-5.750 -0.1494 0.01402 0.00754 -0.0892 0.7629 0.0422
-5.500 -0.1228 0.01365 0.00700 -0.0886 0.7477 0.0427
-5.250 -0.0968 0.01306 0.00633 -0.0881 0.7344 0.0435
-5.000 -0.0698 0.01274 0.00597 -0.0877 0.7225 0.0444
-4.750 -0.0428 0.01250 0.00563 -0.0873 0.7111 0.0454
-4.500 -0.0153 0.01222 0.00529 -0.0869 0.7001 0.0466
-4.250 0.0119 0.01196 0.00492 -0.0865 0.6901 0.0479
-4.000 0.0394 0.01171 0.00468 -0.0862 0.6804 0.0498
-3.750 0.0671 0.01157 0.00447 -0.0859 0.6712 0.0520
-3.500 0.0948 0.01134 0.00425 -0.0856 0.6616 0.0546
-3.250 0.1226 0.01126 0.00410 -0.0853 0.6520 0.0582
-3.000 0.1507 0.01116 0.00403 -0.0850 0.6417 0.0629
-2.750 0.1788 0.01118 0.00401 -0.0847 0.6317 0.0688
-2.500 0.2073 0.01120 0.00401 -0.0845 0.6211 0.0747
-2.250 0.2357 0.01133 0.00409 -0.0843 0.6108 0.0797
-2.000 0.2636 0.01131 0.00406 -0.0841 0.5993 0.0838
-1.750 0.2918 0.01138 0.00409 -0.0839 0.5875 0.0877
-1.500 0.3194 0.01135 0.00397 -0.0836 0.5748 0.0911
-1.250 0.3468 0.01128 0.00389 -0.0833 0.5602 0.0942
-1.000 0.3744 0.01128 0.00385 -0.0830 0.5444 0.0973
-0.750 0.4019 0.01134 0.00381 -0.0827 0.5278 0.0999
-0.500 0.4285 0.01119 0.00361 -0.0823 0.5114 0.1033
-0.250 0.4556 0.01123 0.00361 -0.0820 0.4958 0.1071
0.000 0.4826 0.01132 0.00362 -0.0816 0.4816 0.1107
0.250 0.5095 0.01133 0.00355 -0.0812 0.4686 0.1136
0.500 0.5362 0.01123 0.00343 -0.0809 0.4567 0.1169
0.750 0.5630 0.01127 0.00341 -0.0805 0.4460 0.1195
1.000 0.5902 0.01128 0.00340 -0.0802 0.4368 0.1224
1.250 0.6172 0.01137 0.00341 -0.0799 0.4289 0.1253
1.500 0.6445 0.01132 0.00338 -0.0797 0.4215 0.1295
1.750 0.6713 0.01138 0.00341 -0.0793 0.4142 0.1345
2.000 0.6988 0.01142 0.00345 -0.0791 0.4082 0.1400
2.250 0.7262 0.01142 0.00349 -0.0789 0.4022 0.1503
2.500 0.7530 0.01148 0.00357 -0.0786 0.3967 0.1728
2.750 0.7729 0.01026 0.00380 -0.0776 0.3921 0.7127
3.000 0.8203 0.00983 0.00394 -0.0812 0.3863 1.0000
3.250 0.8462 0.01000 0.00403 -0.0807 0.3816 1.0000
3.500 0.8717 0.01022 0.00416 -0.0801 0.3771 1.0000
3.750 0.8982 0.01035 0.00428 -0.0797 0.3730 1.0000
4.000 0.9247 0.01047 0.00438 -0.0793 0.3683 1.0000
4.250 0.9508 0.01064 0.00450 -0.0788 0.3637 1.0000
4.500 0.9762 0.01087 0.00466 -0.0783 0.3592 1.0000
4.750 1.0027 0.01101 0.00480 -0.0780 0.3554 1.0000
5.000 1.0292 0.01114 0.00493 -0.0776 0.3511 1.0000
5.250 1.0551 0.01131 0.00506 -0.0772 0.3460 1.0000
5.500 1.0800 0.01157 0.00525 -0.0766 0.3405 1.0000
5.750 1.1068 0.01166 0.00538 -0.0763 0.3360 1.0000
6.000 1.1328 0.01181 0.00553 -0.0759 0.3308 1.0000
6.250 1.1578 0.01204 0.00571 -0.0754 0.3255 1.0000
6.500 1.1834 0.01221 0.00589 -0.0750 0.3204 1.0000
6.750 1.2092 0.01237 0.00606 -0.0746 0.3146 1.0000
7.000 1.2338 0.01260 0.00626 -0.0741 0.3088 1.0000
7.250 1.2590 0.01279 0.00646 -0.0736 0.3031 1.0000
7.500 1.2840 0.01299 0.00666 -0.0731 0.2959 1.0000
7.750 1.3078 0.01325 0.00689 -0.0725 0.2880 1.0000
8.000 1.3319 0.01348 0.00712 -0.0719 0.2778 1.0000
8.250 1.3552 0.01377 0.00737 -0.0712 0.2658 1.0000
8.500 1.3769 0.01414 0.00768 -0.0703 0.2499 1.0000
8.750 1.3959 0.01468 0.00809 -0.0691 0.2285 1.0000
9.000 1.4131 0.01533 0.00860 -0.0676 0.2062 1.0000
9.250 1.4295 0.01600 0.00917 -0.0660 0.1917 1.0000
9.500 1.4450 0.01664 0.00976 -0.0642 0.1829 1.0000
9.750 1.4606 0.01720 0.01031 -0.0625 0.1772 1.0000
10.000 1.4741 0.01788 0.01097 -0.0605 0.1721 1.0000
10.250 1.4899 0.01846 0.01157 -0.0589 0.1686 1.0000
10.500 1.5059 0.01905 0.01219 -0.0574 0.1655 1.0000
10.750 1.5200 0.01975 0.01291 -0.0557 0.1625 1.0000
11.000 1.5319 0.02061 0.01377 -0.0539 0.1592 1.0000
11.250 1.5436 0.02150 0.01469 -0.0522 0.1561 1.0000
11.500 1.5600 0.02214 0.01540 -0.0511 0.1538 1.0000
11.750 1.5742 0.02293 0.01625 -0.0499 0.1514 1.0000
12.000 1.5864 0.02389 0.01724 -0.0485 0.1488 1.0000
12.250 1.5960 0.02505 0.01843 -0.0471 0.1461 1.0000
12.500 1.6024 0.02651 0.01991 -0.0455 0.1432 1.0000
12.750 1.6173 0.02739 0.02088 -0.0447 0.1415 1.0000
13.000 1.6308 0.02840 0.02197 -0.0439 0.1393 1.0000
13.250 1.6419 0.02964 0.02328 -0.0431 0.1367 1.0000
13.500 1.6502 0.03116 0.02484 -0.0422 0.1341 1.0000
13.750 1.6547 0.03308 0.02679 -0.0413 0.1314 1.0000
14.000 1.6638 0.03465 0.02844 -0.0407 0.1289 1.0000
14.250 1.6751 0.03605 0.02993 -0.0403 0.1259 1.0000
14.500 1.6817 0.03793 0.03187 -0.0398 0.1225 1.0000
14.750 1.6823 0.04045 0.03442 -0.0393 0.1190 1.0000
15.000 1.6900 0.04230 0.03635 -0.0390 0.1151 1.0000
15.250 1.6924 0.04474 0.03884 -0.0388 0.1102 1.0000
15.500 1.6904 0.04770 0.04184 -0.0386 0.1056 1.0000
15.750 1.6893 0.05064 0.04483 -0.0385 0.0998 1.0000
16.000 1.6831 0.05423 0.04845 -0.0386 0.0947 1.0000
16.250 1.6756 0.05804 0.05231 -0.0388 0.0896 1.0000
16.500 1.6659 0.06221 0.05652 -0.0391 0.0856 1.0000
16.750 1.6563 0.06647 0.06084 -0.0396 0.0821 1.0000
17.000 1.6431 0.07127 0.06569 -0.0403 0.0795 1.0000
17.250 1.6331 0.07574 0.07024 -0.0411 0.0774 1.0000
17.500 1.6235 0.08021 0.07479 -0.0419 0.0757 1.0000
17.750 1.6126 0.08487 0.07951 -0.0428 0.0742 1.0000
18.000 1.6015 0.08960 0.08431 -0.0438 0.0729 1.0000
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