GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 604 AIRFOIL (goe604-il) Reynolds number: 500,000 Max Cl/Cd: 87.75 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe604-il-500000.txt Download as CSV file: xf-goe604-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 604 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6308 0.07578 0.07268 -0.0757 1.0000 0.0290
-15.250 -0.6854 0.06380 0.06044 -0.0848 1.0000 0.0290
-15.000 -0.7224 0.05517 0.05161 -0.0912 1.0000 0.0289
-14.750 -0.7452 0.04908 0.04533 -0.0959 1.0000 0.0290
-14.500 -0.7674 0.04393 0.03999 -0.0993 1.0000 0.0291
-14.250 -0.7865 0.04033 0.03622 -0.1005 1.0000 0.0293
-14.000 -0.8064 0.03775 0.03350 -0.0993 1.0000 0.0294
-13.750 -0.8305 0.03599 0.03165 -0.0956 1.0000 0.0295
-13.500 -0.8362 0.03398 0.02958 -0.0940 0.9985 0.0298
-13.250 -0.8104 0.03245 0.02804 -0.0964 0.9940 0.0304
-13.000 -0.7874 0.03117 0.02671 -0.0980 0.9878 0.0309
-12.750 -0.7625 0.02983 0.02527 -0.0998 0.9823 0.0315
-12.500 -0.7403 0.02848 0.02379 -0.1006 0.9752 0.0321
-12.250 -0.7130 0.02702 0.02216 -0.1023 0.9697 0.0328
-12.000 -0.6857 0.02592 0.02083 -0.1037 0.9627 0.0335
-11.750 -0.6567 0.02418 0.01905 -0.1054 0.9553 0.0344
-11.500 -0.6267 0.02336 0.01823 -0.1065 0.9454 0.0351
-11.250 -0.5965 0.02253 0.01732 -0.1076 0.9341 0.0359
-11.000 -0.5715 0.02176 0.01642 -0.1076 0.9188 0.0367
-10.750 -0.5510 0.02105 0.01556 -0.1065 0.8995 0.0374
-10.500 -0.5316 0.02053 0.01483 -0.1050 0.8765 0.0381
-10.250 -0.5135 0.01956 0.01374 -0.1036 0.8504 0.0389
-10.000 -0.4944 0.01904 0.01313 -0.1020 0.8214 0.0397
-9.750 -0.4756 0.01868 0.01261 -0.1003 0.7899 0.0405
-9.500 -0.4569 0.01831 0.01205 -0.0986 0.7586 0.0413
-9.250 -0.4377 0.01796 0.01150 -0.0969 0.7315 0.0421
-9.000 -0.4174 0.01764 0.01099 -0.0954 0.7089 0.0429
-8.750 -0.3980 0.01706 0.01028 -0.0939 0.6907 0.0439
-8.500 -0.3775 0.01662 0.00977 -0.0926 0.6751 0.0449
-8.250 -0.3558 0.01630 0.00936 -0.0914 0.6616 0.0459
-8.000 -0.3332 0.01596 0.00894 -0.0903 0.6497 0.0470
-7.750 -0.3101 0.01568 0.00853 -0.0893 0.6393 0.0481
-7.500 -0.2872 0.01534 0.00809 -0.0882 0.6291 0.0492
-7.250 -0.2657 0.01485 0.00758 -0.0871 0.6203 0.0507
-7.000 -0.2422 0.01456 0.00724 -0.0861 0.6114 0.0521
-6.750 -0.2183 0.01431 0.00690 -0.0852 0.6036 0.0537
-6.500 -0.1933 0.01409 0.00661 -0.0845 0.5961 0.0551
-6.250 -0.1714 0.01365 0.00615 -0.0833 0.5893 0.0573
-6.000 -0.1466 0.01340 0.00587 -0.0826 0.5830 0.0598
-5.750 -0.1214 0.01319 0.00560 -0.0819 0.5765 0.0622
-5.500 -0.0981 0.01286 0.00524 -0.0809 0.5706 0.0657
-5.250 -0.0725 0.01266 0.00500 -0.0803 0.5652 0.0697
-5.000 -0.0482 0.01232 0.00469 -0.0795 0.5595 0.0762
-4.750 -0.0239 0.01205 0.00442 -0.0787 0.5539 0.0868
-4.500 0.0000 0.01172 0.00425 -0.0779 0.5486 0.1165
-4.250 0.0263 0.01157 0.00419 -0.0774 0.5432 0.1438
-4.000 0.0527 0.01150 0.00411 -0.0769 0.5379 0.1578
-3.750 0.0792 0.01151 0.00405 -0.0765 0.5328 0.1676
-3.500 0.1056 0.01140 0.00398 -0.0760 0.5281 0.1774
-3.250 0.1323 0.01133 0.00389 -0.0756 0.5229 0.1851
-3.000 0.1582 0.01127 0.00381 -0.0751 0.5176 0.1938
-2.750 0.1846 0.01125 0.00375 -0.0746 0.5125 0.2018
-2.500 0.2109 0.01114 0.00369 -0.0741 0.5074 0.2119
-2.250 0.2370 0.01107 0.00362 -0.0736 0.5022 0.2226
-2.000 0.2627 0.01104 0.00358 -0.0731 0.4972 0.2375
-1.750 0.2887 0.01095 0.00356 -0.0726 0.4926 0.2571
-1.500 0.3144 0.01083 0.00354 -0.0721 0.4874 0.2827
-1.250 0.3396 0.01075 0.00352 -0.0714 0.4823 0.3133
-1.000 0.3645 0.01070 0.00352 -0.0708 0.4773 0.3454
-0.750 0.3899 0.01057 0.00351 -0.0702 0.4723 0.3767
-0.500 0.4147 0.01048 0.00350 -0.0695 0.4668 0.4102
-0.250 0.4384 0.01042 0.00350 -0.0686 0.4614 0.4517
0.000 0.4620 0.01023 0.00352 -0.0677 0.4562 0.5091
0.250 0.4833 0.01001 0.00355 -0.0663 0.4508 0.5895
0.500 0.5019 0.00977 0.00360 -0.0643 0.4457 0.6891
0.750 0.5210 0.00954 0.00371 -0.0622 0.4409 0.7959
1.000 0.5553 0.00946 0.00388 -0.0630 0.4349 0.8916
1.250 0.6129 0.00970 0.00407 -0.0690 0.4280 0.9383
1.500 0.6623 0.00989 0.00422 -0.0734 0.4217 0.9571
1.750 0.7018 0.01007 0.00434 -0.0757 0.4154 0.9698
2.000 0.7389 0.01032 0.00447 -0.0776 0.4088 0.9802
2.250 0.7845 0.01044 0.00456 -0.0813 0.4019 0.9860
2.500 0.8279 0.01065 0.00468 -0.0846 0.3953 0.9931
2.750 0.8781 0.01083 0.00479 -0.0893 0.3896 0.9987
3.000 0.9068 0.01093 0.00487 -0.0896 0.3847 1.0000
3.250 0.9252 0.01107 0.00496 -0.0879 0.3806 1.0000
3.500 0.9427 0.01127 0.00508 -0.0860 0.3763 1.0000
3.750 0.9625 0.01137 0.00519 -0.0845 0.3727 1.0000
4.000 0.9818 0.01149 0.00530 -0.0829 0.3687 1.0000
4.250 1.0003 0.01166 0.00542 -0.0811 0.3646 1.0000
4.500 1.0182 0.01188 0.00558 -0.0793 0.3609 1.0000
4.750 1.0376 0.01205 0.00574 -0.0777 0.3579 1.0000
5.000 1.0576 0.01219 0.00589 -0.0763 0.3551 1.0000
5.250 1.0772 0.01235 0.00605 -0.0747 0.3521 1.0000
5.500 1.0962 0.01254 0.00622 -0.0731 0.3492 1.0000
5.750 1.1146 0.01276 0.00640 -0.0714 0.3464 1.0000
6.000 1.1330 0.01306 0.00664 -0.0698 0.3432 1.0000
6.250 1.1527 0.01320 0.00683 -0.0683 0.3411 1.0000
6.500 1.1718 0.01337 0.00703 -0.0668 0.3384 1.0000
6.750 1.1890 0.01355 0.00722 -0.0649 0.3355 1.0000
7.000 1.2048 0.01376 0.00741 -0.0627 0.3327 1.0000
7.250 1.2205 0.01401 0.00764 -0.0606 0.3302 1.0000
7.500 1.2376 0.01434 0.00793 -0.0589 0.3272 1.0000
7.750 1.2551 0.01453 0.00817 -0.0571 0.3253 1.0000
8.000 1.2726 0.01474 0.00843 -0.0555 0.3229 1.0000
8.250 1.2902 0.01497 0.00869 -0.0539 0.3203 1.0000
8.500 1.3071 0.01524 0.00897 -0.0522 0.3172 1.0000
8.750 1.3235 0.01557 0.00928 -0.0506 0.3144 1.0000
9.000 1.3407 0.01598 0.00966 -0.0491 0.3115 1.0000
9.250 1.3585 0.01627 0.01002 -0.0478 0.3094 1.0000
9.500 1.3760 0.01657 0.01038 -0.0465 0.3069 1.0000
9.750 1.3933 0.01691 0.01077 -0.0452 0.3043 1.0000
10.000 1.4099 0.01729 0.01118 -0.0438 0.3016 1.0000
10.250 1.4253 0.01775 0.01163 -0.0424 0.2987 1.0000
10.500 1.4405 0.01829 0.01216 -0.0410 0.2955 1.0000
10.750 1.4567 0.01872 0.01268 -0.0398 0.2930 1.0000
11.000 1.4728 0.01919 0.01322 -0.0387 0.2900 1.0000
11.250 1.4875 0.01974 0.01381 -0.0375 0.2865 1.0000
11.500 1.5007 0.02040 0.01449 -0.0362 0.2831 1.0000
11.750 1.5123 0.02119 0.01529 -0.0348 0.2792 1.0000
12.000 1.5270 0.02184 0.01604 -0.0339 0.2750 1.0000
12.250 1.5383 0.02272 0.01695 -0.0327 0.2695 1.0000
12.500 1.5453 0.02391 0.01814 -0.0314 0.2639 1.0000
12.750 1.5577 0.02486 0.01918 -0.0306 0.2575 1.0000
13.000 1.5620 0.02639 0.02071 -0.0294 0.2505 1.0000
13.250 1.5704 0.02775 0.02213 -0.0286 0.2423 1.0000
13.500 1.5705 0.02982 0.02420 -0.0276 0.2329 1.0000
13.750 1.5682 0.03221 0.02659 -0.0267 0.2224 1.0000
14.000 1.5654 0.03475 0.02914 -0.0260 0.2121 1.0000
14.250 1.5556 0.03802 0.03240 -0.0252 0.2021 1.0000
14.500 1.5477 0.04120 0.03559 -0.0246 0.1959 1.0000
14.750 1.5401 0.04441 0.03882 -0.0242 0.1901 1.0000
15.000 1.5334 0.04759 0.04204 -0.0238 0.1857 1.0000
15.250 1.5244 0.05104 0.04551 -0.0235 0.1822 1.0000
15.500 1.5208 0.05398 0.04849 -0.0233 0.1791 1.0000
15.750 1.5200 0.05670 0.05127 -0.0232 0.1766 1.0000
16.000 1.5150 0.05987 0.05450 -0.0232 0.1736 1.0000
16.250 1.5109 0.06297 0.05762 -0.0232 0.1712 1.0000
16.500 1.5046 0.06630 0.06095 -0.0232 0.1681 1.0000
16.750 1.5051 0.06900 0.06372 -0.0234 0.1660 1.0000
17.000 1.5066 0.07159 0.06639 -0.0236 0.1643 1.0000
17.250 1.5063 0.07441 0.06929 -0.0238 0.1622 1.0000
17.500 1.5036 0.07751 0.07243 -0.0241 0.1597 1.0000
17.750 1.5044 0.08019 0.07514 -0.0244 0.1582 1.0000
18.000 1.5028 0.08308 0.07804 -0.0246 0.1555 1.0000
18.250 1.5068 0.08532 0.08031 -0.0248 0.1536 1.0000
18.500 1.5055 0.08844 0.08355 -0.0254 0.1521 1.0000
18.750 1.5042 0.09156 0.08677 -0.0261 0.1501 1.0000
19.000 1.5033 0.09462 0.08989 -0.0267 0.1481 1.0000
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