GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 383 AIRFOIL (goe383-il) Reynolds number: 500,000 Max Cl/Cd: 83.12 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe383-il-500000-n5.txt Download as CSV file: xf-goe383-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 383 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.6511 0.08575 0.08215 -0.0776 0.9746 0.0294
-16.000 -0.7454 0.06260 0.05839 -0.0944 0.9566 0.0295
-15.750 -0.7649 0.05649 0.05206 -0.0985 0.9469 0.0296
-15.500 -0.7789 0.05159 0.04698 -0.1014 0.9366 0.0296
-15.250 -0.7882 0.04744 0.04265 -0.1038 0.9256 0.0297
-15.000 -0.7943 0.04398 0.03903 -0.1053 0.9140 0.0297
-14.750 -0.7979 0.04104 0.03592 -0.1062 0.9004 0.0298
-14.500 -0.7993 0.03850 0.03320 -0.1067 0.8844 0.0299
-14.250 -0.7982 0.03631 0.03082 -0.1067 0.8669 0.0299
-14.000 -0.7952 0.03441 0.02873 -0.1065 0.8486 0.0300
-13.750 -0.7900 0.03275 0.02689 -0.1060 0.8305 0.0301
-13.500 -0.7830 0.03132 0.02526 -0.1054 0.8129 0.0301
-13.250 -0.7746 0.03000 0.02377 -0.1045 0.7959 0.0302
-12.750 -0.7533 0.02767 0.02118 -0.1025 0.7634 0.0305
-12.500 -0.7403 0.02672 0.02012 -0.1014 0.7496 0.0306
-12.000 -0.7127 0.02516 0.01836 -0.0987 0.7243 0.0308
-11.750 -0.6983 0.02453 0.01762 -0.0972 0.7133 0.0309
-11.500 -0.6804 0.02387 0.01688 -0.0962 0.7034 0.0311
-11.250 -0.6616 0.02327 0.01619 -0.0953 0.6941 0.0312
-11.000 -0.6419 0.02268 0.01552 -0.0944 0.6866 0.0314
-10.750 -0.6214 0.02211 0.01487 -0.0936 0.6792 0.0316
-10.500 -0.6005 0.02157 0.01425 -0.0928 0.6725 0.0318
-10.250 -0.5788 0.02104 0.01365 -0.0921 0.6669 0.0320
-10.000 -0.5566 0.02053 0.01307 -0.0914 0.6612 0.0322
-9.750 -0.5341 0.02004 0.01251 -0.0908 0.6557 0.0324
-9.500 -0.5112 0.01958 0.01197 -0.0901 0.6509 0.0326
-9.250 -0.4878 0.01913 0.01146 -0.0896 0.6469 0.0329
-9.000 -0.4639 0.01869 0.01096 -0.0890 0.6430 0.0331
-8.750 -0.4397 0.01828 0.01049 -0.0885 0.6383 0.0334
-8.500 -0.4152 0.01791 0.01005 -0.0880 0.6332 0.0337
-8.250 -0.3904 0.01760 0.00965 -0.0876 0.6282 0.0339
-8.000 -0.3666 0.01714 0.00917 -0.0870 0.6242 0.0343
-7.750 -0.3417 0.01675 0.00878 -0.0866 0.6204 0.0346
-7.500 -0.3163 0.01641 0.00842 -0.0862 0.6160 0.0349
-7.250 -0.2908 0.01610 0.00808 -0.0858 0.6121 0.0353
-7.000 -0.2651 0.01582 0.00776 -0.0855 0.6086 0.0356
-6.750 -0.2393 0.01555 0.00745 -0.0851 0.6053 0.0360
-6.500 -0.2131 0.01528 0.00715 -0.0848 0.6023 0.0364
-6.250 -0.1866 0.01501 0.00686 -0.0846 0.5997 0.0368
-6.000 -0.1598 0.01475 0.00659 -0.0844 0.5970 0.0373
-5.750 -0.1330 0.01452 0.00633 -0.0842 0.5942 0.0378
-5.500 -0.1064 0.01426 0.00606 -0.0839 0.5913 0.0382
-5.250 -0.0798 0.01402 0.00581 -0.0837 0.5882 0.0388
-5.000 -0.0529 0.01383 0.00560 -0.0835 0.5850 0.0395
-4.750 -0.0259 0.01368 0.00541 -0.0833 0.5816 0.0402
-4.500 0.0017 0.01348 0.00522 -0.0832 0.5790 0.0410
-4.250 0.0295 0.01332 0.00505 -0.0831 0.5761 0.0419
-4.000 0.0570 0.01313 0.00487 -0.0830 0.5730 0.0430
-3.750 0.0845 0.01297 0.00472 -0.0829 0.5697 0.0443
-3.500 0.1122 0.01284 0.00457 -0.0828 0.5664 0.0458
-3.250 0.1397 0.01272 0.00443 -0.0827 0.5630 0.0473
-3.000 0.1672 0.01259 0.00429 -0.0826 0.5596 0.0493
-2.500 0.2230 0.01231 0.00405 -0.0825 0.5518 0.0553
-2.250 0.2505 0.01218 0.00393 -0.0824 0.5476 0.0608
-2.000 0.2766 0.01191 0.00379 -0.0821 0.5435 0.0887
-1.750 0.3032 0.01172 0.00372 -0.0819 0.5396 0.1265
-1.500 0.3308 0.01156 0.00366 -0.0819 0.5353 0.1477
-1.250 0.3582 0.01142 0.00360 -0.0818 0.5302 0.1696
-1.000 0.3847 0.01125 0.00354 -0.0816 0.5249 0.2038
-0.750 0.4110 0.01108 0.00352 -0.0814 0.5195 0.2547
-0.500 0.4381 0.01094 0.00350 -0.0814 0.5129 0.2946
-0.250 0.4644 0.01084 0.00348 -0.0811 0.5057 0.3277
0.000 0.4909 0.01073 0.00348 -0.0809 0.4992 0.3671
0.250 0.5161 0.01050 0.00348 -0.0806 0.4916 0.4406
0.500 0.5396 0.01024 0.00352 -0.0799 0.4844 0.5378
0.750 0.5637 0.01005 0.00362 -0.0792 0.4767 0.6278
1.000 0.5887 0.01008 0.00370 -0.0786 0.4685 0.6711
1.250 0.6149 0.01013 0.00378 -0.0783 0.4609 0.6957
1.500 0.6407 0.01023 0.00387 -0.0779 0.4532 0.7158
1.750 0.6661 0.01030 0.00398 -0.0774 0.4471 0.7386
2.000 0.6919 0.01037 0.00409 -0.0770 0.4412 0.7612
2.250 0.7166 0.01046 0.00422 -0.0764 0.4352 0.7849
2.500 0.7409 0.01057 0.00437 -0.0757 0.4299 0.8099
2.750 0.7661 0.01065 0.00451 -0.0751 0.4250 0.8326
3.000 0.7901 0.01078 0.00467 -0.0743 0.4194 0.8571
3.500 0.8367 0.01110 0.00503 -0.0725 0.4072 0.9085
3.750 0.8620 0.01128 0.00522 -0.0720 0.4014 0.9302
4.000 0.8902 0.01152 0.00543 -0.0723 0.3967 0.9505
4.250 0.9225 0.01175 0.00563 -0.0734 0.3929 0.9673
4.500 0.9586 0.01194 0.00583 -0.0753 0.3892 0.9815
4.750 0.9960 0.01218 0.00604 -0.0776 0.3852 0.9927
5.000 1.0334 0.01244 0.00628 -0.0800 0.3812 0.9995
5.250 1.0460 0.01264 0.00643 -0.0773 0.3779 1.0000
5.500 1.0588 0.01282 0.00660 -0.0746 0.3748 1.0000
5.750 1.0771 0.01299 0.00678 -0.0730 0.3718 1.0000
6.000 1.0963 0.01319 0.00699 -0.0717 0.3686 1.0000
6.250 1.1156 0.01344 0.00723 -0.0704 0.3653 1.0000
6.500 1.1345 0.01374 0.00750 -0.0691 0.3618 1.0000
6.750 1.1527 0.01409 0.00783 -0.0678 0.3582 1.0000
7.000 1.1743 0.01435 0.00811 -0.0671 0.3550 1.0000
7.250 1.1955 0.01464 0.00842 -0.0663 0.3512 1.0000
7.500 1.2154 0.01499 0.00877 -0.0654 0.3474 1.0000
7.750 1.2343 0.01540 0.00917 -0.0644 0.3435 1.0000
8.000 1.2524 0.01586 0.00962 -0.0634 0.3397 1.0000
8.250 1.2733 0.01623 0.01001 -0.0627 0.3353 1.0000
8.500 1.2915 0.01671 0.01050 -0.0618 0.3296 1.0000
8.750 1.3070 0.01735 0.01110 -0.0606 0.3242 1.0000
9.000 1.3261 0.01784 0.01162 -0.0598 0.3192 1.0000
9.250 1.3429 0.01846 0.01225 -0.0589 0.3131 1.0000
9.500 1.3566 0.01927 0.01304 -0.0577 0.3070 1.0000
9.750 1.3734 0.01995 0.01373 -0.0569 0.3000 1.0000
10.000 1.3850 0.02095 0.01471 -0.0556 0.2927 1.0000
10.250 1.3996 0.02181 0.01558 -0.0547 0.2860 1.0000
10.500 1.4096 0.02300 0.01675 -0.0535 0.2780 1.0000
10.750 1.4202 0.02418 0.01793 -0.0524 0.2696 1.0000
11.000 1.4265 0.02571 0.01943 -0.0511 0.2611 1.0000
11.250 1.4349 0.02713 0.02085 -0.0500 0.2523 1.0000
11.500 1.4406 0.02880 0.02250 -0.0489 0.2450 1.0000
11.750 1.4473 0.03045 0.02415 -0.0479 0.2375 1.0000
12.000 1.4514 0.03235 0.02604 -0.0468 0.2307 1.0000
12.250 1.4574 0.03414 0.02784 -0.0459 0.2237 1.0000
12.500 1.4600 0.03625 0.02994 -0.0450 0.2177 1.0000
12.750 1.4670 0.03802 0.03174 -0.0443 0.2124 1.0000
13.000 1.4715 0.04003 0.03376 -0.0435 0.2075 1.0000
13.250 1.4754 0.04214 0.03589 -0.0428 0.2034 1.0000
13.500 1.4827 0.04394 0.03773 -0.0423 0.1992 1.0000
13.750 1.4863 0.04612 0.03993 -0.0417 0.1948 1.0000
14.000 1.4876 0.04853 0.04236 -0.0411 0.1908 1.0000
14.250 1.4950 0.05039 0.04428 -0.0407 0.1875 1.0000
14.500 1.5006 0.05244 0.04635 -0.0403 0.1836 1.0000
14.750 1.5014 0.05500 0.04894 -0.0398 0.1798 1.0000
15.000 1.5051 0.05727 0.05125 -0.0395 0.1763 1.0000
15.250 1.5085 0.05961 0.05364 -0.0392 0.1721 1.0000
15.500 1.5088 0.06230 0.05635 -0.0388 0.1674 1.0000
15.750 1.5091 0.06505 0.05914 -0.0386 0.1632 1.0000
16.000 1.5098 0.06774 0.06187 -0.0384 0.1577 1.0000
16.250 1.5058 0.07101 0.06516 -0.0382 0.1524 1.0000
16.500 1.5034 0.07414 0.06832 -0.0381 0.1455 1.0000
16.750 1.4971 0.07779 0.07198 -0.0381 0.1380 1.0000
17.000 1.4852 0.08213 0.07632 -0.0382 0.1274 1.0000
17.250 1.4544 0.08884 0.08294 -0.0384 0.1041 1.0000
17.500 1.4208 0.09610 0.09012 -0.0389 0.0844 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 383 AIRFOIL (goe383-il)