GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 200,000 Max Cl/Cd: 66.31 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe645-il-200000.txt Download as CSV file: xf-goe645-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6730 0.05019 0.04589 -0.0839 1.0000 0.0508
-11.250 -0.7005 0.04759 0.04316 -0.0807 1.0000 0.0507
-11.000 -0.7271 0.04549 0.04093 -0.0765 1.0000 0.0507
-10.750 -0.7442 0.04284 0.03810 -0.0739 0.9988 0.0509
-10.500 -0.7134 0.03944 0.03464 -0.0782 0.9932 0.0523
-10.250 -0.6806 0.03723 0.03234 -0.0817 0.9861 0.0537
-10.000 -0.6511 0.03423 0.02899 -0.0854 0.9785 0.0550
-9.750 -0.6209 0.03142 0.02575 -0.0885 0.9706 0.0563
-9.500 -0.5915 0.02943 0.02329 -0.0906 0.9615 0.0576
-9.250 -0.5561 0.02710 0.02093 -0.0933 0.9562 0.0595
-9.000 -0.5231 0.02575 0.01951 -0.0949 0.9481 0.0611
-8.750 -0.4859 0.02429 0.01787 -0.0972 0.9423 0.0630
-8.500 -0.4474 0.02300 0.01633 -0.0995 0.9368 0.0652
-8.250 -0.4152 0.02158 0.01491 -0.1007 0.9279 0.0675
-8.000 -0.3748 0.02053 0.01384 -0.1032 0.9228 0.0702
-7.750 -0.3449 0.01968 0.01287 -0.1036 0.9110 0.0729
-7.500 -0.3112 0.01874 0.01191 -0.1047 0.9018 0.0762
-7.250 -0.2788 0.01812 0.01125 -0.1055 0.8911 0.0803
-7.000 -0.2505 0.01746 0.01051 -0.1054 0.8787 0.0848
-6.750 -0.2205 0.01698 0.00999 -0.1056 0.8674 0.0909
-6.500 -0.1933 0.01647 0.00943 -0.1052 0.8550 0.0995
-6.250 -0.1689 0.01594 0.00889 -0.1044 0.8419 0.1126
-6.000 -0.1431 0.01546 0.00831 -0.1038 0.8301 0.1327
-5.750 -0.1173 0.01510 0.00796 -0.1033 0.8183 0.1501
-5.500 -0.0922 0.01499 0.00777 -0.1025 0.8051 0.1634
-5.250 -0.0658 0.01491 0.00763 -0.1019 0.7933 0.1746
-5.000 -0.0390 0.01480 0.00746 -0.1013 0.7820 0.1841
-4.750 -0.0135 0.01474 0.00728 -0.1005 0.7691 0.1939
-4.500 0.0126 0.01470 0.00721 -0.0999 0.7572 0.2035
-4.250 0.0392 0.01464 0.00706 -0.0993 0.7456 0.2139
-4.000 0.0648 0.01464 0.00696 -0.0985 0.7328 0.2254
-3.750 0.0909 0.01462 0.00695 -0.0978 0.7212 0.2367
-3.500 0.1172 0.01463 0.00689 -0.0971 0.7097 0.2498
-3.250 0.1425 0.01464 0.00686 -0.0963 0.6968 0.2637
-3.000 0.1688 0.01473 0.00680 -0.0956 0.6854 0.2773
-2.750 0.1949 0.01465 0.00673 -0.0950 0.6742 0.2883
-2.500 0.2206 0.01460 0.00662 -0.0943 0.6622 0.2991
-2.250 0.2471 0.01461 0.00653 -0.0937 0.6516 0.3092
-2.000 0.2731 0.01453 0.00641 -0.0931 0.6403 0.3182
-1.750 0.2993 0.01453 0.00635 -0.0925 0.6295 0.3273
-1.500 0.3261 0.01448 0.00619 -0.0920 0.6198 0.3357
-1.250 0.3516 0.01444 0.00614 -0.0913 0.6081 0.3440
-1.000 0.3778 0.01441 0.00600 -0.0907 0.5974 0.3522
-0.750 0.4037 0.01435 0.00590 -0.0901 0.5863 0.3603
-0.500 0.4294 0.01434 0.00583 -0.0894 0.5752 0.3692
-0.250 0.4560 0.01434 0.00577 -0.0890 0.5666 0.3787
0.000 0.4814 0.01432 0.00578 -0.0883 0.5571 0.3894
0.500 0.5336 0.01432 0.00578 -0.0873 0.5406 0.4106
0.750 0.5603 0.01437 0.00575 -0.0869 0.5332 0.4232
1.000 0.5854 0.01435 0.00583 -0.0863 0.5251 0.4376
1.250 0.6109 0.01433 0.00583 -0.0856 0.5170 0.4547
1.500 0.6357 0.01432 0.00590 -0.0849 0.5086 0.4757
1.750 0.6600 0.01424 0.00594 -0.0841 0.5003 0.5045
2.000 0.6832 0.01412 0.00603 -0.0831 0.4924 0.5584
2.250 0.7586 0.01333 0.00614 -0.0924 0.4812 1.0000
2.500 0.7821 0.01351 0.00625 -0.0914 0.4736 1.0000
2.750 0.8059 0.01369 0.00634 -0.0905 0.4663 1.0000
3.000 0.8300 0.01392 0.00646 -0.0897 0.4594 1.0000
3.250 0.8530 0.01409 0.00660 -0.0886 0.4517 1.0000
3.500 0.8777 0.01435 0.00670 -0.0879 0.4451 1.0000
3.750 0.8999 0.01452 0.00690 -0.0868 0.4374 1.0000
4.000 0.9235 0.01473 0.00703 -0.0859 0.4305 1.0000
4.250 0.9467 0.01497 0.00724 -0.0849 0.4234 1.0000
4.500 0.9693 0.01517 0.00742 -0.0839 0.4158 1.0000
4.750 0.9927 0.01544 0.00759 -0.0830 0.4088 1.0000
5.000 1.0142 0.01563 0.00781 -0.0817 0.4005 1.0000
5.250 1.0378 0.01592 0.00797 -0.0809 0.3938 1.0000
5.500 1.0589 0.01614 0.00826 -0.0796 0.3860 1.0000
5.750 1.0812 0.01641 0.00847 -0.0786 0.3793 1.0000
6.000 1.1029 0.01670 0.00876 -0.0775 0.3722 1.0000
6.250 1.1242 0.01697 0.00902 -0.0763 0.3652 1.0000
6.500 1.1467 0.01732 0.00929 -0.0754 0.3594 1.0000
6.750 1.1670 0.01760 0.00965 -0.0741 0.3525 1.0000
7.000 1.1883 0.01792 0.00992 -0.0730 0.3466 1.0000
7.250 1.2095 0.01829 0.01027 -0.0719 0.3411 1.0000
7.500 1.2291 0.01861 0.01065 -0.0705 0.3350 1.0000
7.750 1.2494 0.01895 0.01093 -0.0693 0.3295 1.0000
8.000 1.2684 0.01932 0.01133 -0.0679 0.3237 1.0000
8.250 1.2868 0.01966 0.01173 -0.0663 0.3183 1.0000
8.500 1.3063 0.02005 0.01208 -0.0651 0.3137 1.0000
8.750 1.3253 0.02048 0.01252 -0.0637 0.3093 1.0000
9.000 1.3419 0.02087 0.01300 -0.0619 0.3047 1.0000
9.250 1.3580 0.02127 0.01342 -0.0601 0.3005 1.0000
9.500 1.3768 0.02173 0.01383 -0.0588 0.2966 1.0000
9.750 1.3906 0.02219 0.01438 -0.0567 0.2923 1.0000
10.000 1.4030 0.02264 0.01492 -0.0544 0.2875 1.0000
10.250 1.4176 0.02312 0.01541 -0.0526 0.2832 1.0000
10.500 1.4351 0.02368 0.01592 -0.0513 0.2793 1.0000
10.750 1.4453 0.02426 0.01665 -0.0489 0.2750 1.0000
11.000 1.4568 0.02486 0.01734 -0.0469 0.2705 1.0000
11.250 1.4706 0.02548 0.01794 -0.0453 0.2662 1.0000
11.500 1.4817 0.02622 0.01874 -0.0434 0.2617 1.0000
11.750 1.4893 0.02703 0.01968 -0.0413 0.2567 1.0000
12.000 1.4988 0.02785 0.02052 -0.0395 0.2518 1.0000
12.250 1.5078 0.02880 0.02149 -0.0377 0.2466 1.0000
12.500 1.5114 0.02995 0.02279 -0.0357 0.2409 1.0000
12.750 1.5182 0.03106 0.02386 -0.0340 0.2350 1.0000
13.000 1.5203 0.03251 0.02543 -0.0322 0.2288 1.0000
13.250 1.5213 0.03408 0.02706 -0.0306 0.2221 1.0000
13.500 1.5246 0.03566 0.02864 -0.0293 0.2160 1.0000
13.750 1.5231 0.03764 0.03075 -0.0280 0.2094 1.0000
14.000 1.5268 0.03931 0.03233 -0.0269 0.2036 1.0000
14.250 1.5247 0.04159 0.03479 -0.0260 0.1979 1.0000
14.500 1.5250 0.04373 0.03698 -0.0252 0.1928 1.0000
14.750 1.5296 0.04551 0.03871 -0.0244 0.1887 1.0000
15.000 1.5284 0.04801 0.04139 -0.0240 0.1845 1.0000
15.250 1.5285 0.05042 0.04390 -0.0236 0.1804 1.0000
15.500 1.5313 0.05258 0.04607 -0.0233 0.1772 1.0000
15.750 1.5352 0.05466 0.04816 -0.0230 0.1742 1.0000
16.000 1.5343 0.05742 0.05109 -0.0230 0.1713 1.0000
16.250 1.5330 0.06027 0.05406 -0.0231 0.1680 1.0000
16.500 1.5326 0.06303 0.05688 -0.0233 0.1650 1.0000
16.750 1.5352 0.06539 0.05919 -0.0234 0.1616 1.0000
17.000 1.5297 0.06901 0.06300 -0.0240 0.1588 1.0000
17.250 1.5243 0.07267 0.06679 -0.0248 0.1555 1.0000
17.500 1.5216 0.07598 0.07015 -0.0255 0.1524 1.0000
17.750 1.5252 0.07831 0.07241 -0.0257 0.1490 1.0000
18.000 1.5165 0.08264 0.07694 -0.0269 0.1465 1.0000
18.250 1.5090 0.08685 0.08129 -0.0282 0.1436 1.0000
18.500 1.5050 0.09051 0.08503 -0.0292 0.1407 1.0000
18.750 1.5102 0.09268 0.08712 -0.0296 0.1374 1.0000
19.000 1.5047 0.09665 0.09123 -0.0308 0.1349 1.0000
19.250 1.4958 0.10125 0.09599 -0.0324 0.1326 1.0000
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