GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 525 AIRFOIL (goe525-il) Reynolds number: 200,000 Max Cl/Cd: 74.29 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe525-il-200000.txt Download as CSV file: xf-goe525-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 525 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
------ -------- --------- --------- -------- -------- --------
-10.000 0.1678 0.11355 0.10977 -0.1222 0.9016 0.0566
-9.750 0.1832 0.11033 0.10654 -0.1258 0.8987 0.0588
-9.500 0.1810 0.10734 0.10355 -0.1335 0.8957 0.0605
-9.250 0.2181 0.10274 0.09892 -0.1349 0.8952 0.0613
-9.000 0.2190 0.10150 0.09771 -0.1316 0.8859 0.0623
-8.750 0.2389 0.09850 0.09469 -0.1344 0.8830 0.0643
-8.500 0.2405 0.09578 0.09196 -0.1421 0.8796 0.0681
-8.000 0.2676 0.08950 0.08569 -0.1421 0.8684 0.0695
-7.750 0.2996 0.08599 0.08215 -0.1451 0.8668 0.0712
-7.500 0.3266 0.08250 0.07862 -0.1498 0.8648 0.0740
-7.250 0.3052 0.08145 0.07760 -0.1498 0.8531 0.0771
-7.000 0.3716 0.07488 0.07094 -0.1613 0.8597 0.0795
-6.750 0.3649 0.07405 0.07015 -0.1564 0.8484 0.0805
-6.500 0.3962 0.07079 0.06684 -0.1615 0.8462 0.0839
-6.250 0.3739 0.07021 0.06630 -0.1562 0.8332 0.0860
-6.000 0.3844 0.06567 0.06172 -0.1642 0.8284 0.0891
-5.500 0.4115 0.06237 0.05841 -0.1609 0.8138 0.0922
-5.250 0.3963 0.05942 0.05545 -0.1692 0.7990 0.0995
-5.000 0.4283 0.05566 0.05164 -0.1712 0.7963 0.1012
-4.750 0.5817 0.02617 0.02023 -0.2412 0.7940 0.0681
-4.500 0.6066 0.02439 0.01824 -0.2422 0.7839 0.0676
-4.250 0.5833 0.03283 0.02801 -0.2240 0.7774 0.1017
-4.000 0.7068 0.02071 0.01380 -0.2525 0.7739 0.0691
-3.750 0.7349 0.01989 0.01292 -0.2528 0.7648 0.0706
-3.500 0.7806 0.01886 0.01170 -0.2563 0.7596 0.0723
-3.250 0.8036 0.01844 0.01122 -0.2554 0.7496 0.0738
-3.000 0.8439 0.01776 0.01036 -0.2577 0.7433 0.0764
-2.750 0.8702 0.01732 0.00991 -0.2575 0.7339 0.0792
-2.500 0.9070 0.01688 0.00942 -0.2592 0.7265 0.0850
-2.250 0.9353 0.01659 0.00913 -0.2594 0.7172 0.0914
-2.000 0.9721 0.01622 0.00874 -0.2612 0.7096 0.1043
-1.750 1.0033 0.01596 0.00857 -0.2621 0.7007 0.1445
-1.500 1.0401 0.01561 0.00834 -0.2642 0.6924 0.2181
-1.250 1.0676 0.01563 0.00844 -0.2643 0.6833 0.2684
-1.000 1.0990 0.01565 0.00843 -0.2650 0.6750 0.3173
-0.750 1.1253 0.01578 0.00862 -0.2648 0.6663 0.3636
-0.500 1.1537 0.01594 0.00877 -0.2648 0.6578 0.4093
-0.250 1.1784 0.01618 0.00902 -0.2641 0.6491 0.4422
0.000 1.2045 0.01643 0.00921 -0.2636 0.6404 0.4708
0.250 1.2298 0.01672 0.00944 -0.2630 0.6321 0.4935
0.500 1.2534 0.01698 0.00966 -0.2621 0.6234 0.5123
0.750 1.2794 0.01729 0.00990 -0.2616 0.6154 0.5303
1.000 1.2999 0.01757 0.01018 -0.2601 0.6065 0.5454
1.250 1.3280 0.01788 0.01037 -0.2601 0.5989 0.5612
1.500 1.3457 0.01818 0.01069 -0.2581 0.5901 0.5762
1.750 1.3743 0.01850 0.01087 -0.2582 0.5827 0.5931
2.000 1.3887 0.01882 0.01126 -0.2556 0.5741 0.6058
2.250 1.4121 0.01908 0.01145 -0.2547 0.5666 0.6185
2.500 1.4317 0.01940 0.01175 -0.2532 0.5588 0.6321
2.750 1.4501 0.01968 0.01201 -0.2515 0.5510 0.6466
3.000 1.4741 0.01995 0.01221 -0.2508 0.5442 0.6583
3.250 1.4864 0.02022 0.01252 -0.2480 0.5363 0.6680
3.500 1.5108 0.02047 0.01266 -0.2475 0.5296 0.6792
3.750 1.5260 0.02079 0.01302 -0.2453 0.5225 0.6881
4.000 1.5438 0.02110 0.01330 -0.2436 0.5156 0.6987
4.250 1.5702 0.02137 0.01347 -0.2436 0.5096 0.7086
4.500 1.5824 0.02177 0.01395 -0.2410 0.5027 0.7172
4.750 1.6027 0.02209 0.01423 -0.2399 0.4965 0.7270
5.000 1.6270 0.02243 0.01451 -0.2395 0.4908 0.7366
5.250 1.6417 0.02290 0.01504 -0.2375 0.4845 0.7464
5.500 1.6626 0.02324 0.01535 -0.2366 0.4789 0.7560
5.750 1.6876 0.02362 0.01567 -0.2365 0.4734 0.7671
6.250 1.7187 0.02454 0.01666 -0.2329 0.4618 0.7932
6.500 1.7451 0.02488 0.01693 -0.2330 0.4566 0.8076
6.750 1.7550 0.02547 0.01765 -0.2303 0.4510 0.8216
7.000 1.7713 0.02590 0.01816 -0.2288 0.4458 0.8426
7.250 1.7959 0.02610 0.01832 -0.2285 0.4410 1.0000
7.500 1.8094 0.02687 0.01916 -0.2267 0.4359 1.0000
7.750 1.8241 0.02760 0.01993 -0.2251 0.4306 1.0000
8.000 1.8460 0.02817 0.02045 -0.2246 0.4257 1.0000
8.250 1.8710 0.02876 0.02098 -0.2247 0.4209 1.0000
8.500 1.8782 0.02971 0.02204 -0.2220 0.4158 1.0000
8.750 1.8930 0.03046 0.02279 -0.2205 0.4106 1.0000
9.000 1.9229 0.03087 0.02306 -0.2212 0.4054 1.0000
9.250 1.9238 0.03207 0.02442 -0.2177 0.4003 1.0000
9.500 1.9329 0.03304 0.02545 -0.2155 0.3950 1.0000
9.750 1.9517 0.03371 0.02607 -0.2146 0.3903 1.0000
10.000 1.9700 0.03452 0.02689 -0.2138 0.3857 1.0000
10.250 1.9728 0.03585 0.02836 -0.2109 0.3809 1.0000
10.500 1.9841 0.03685 0.02940 -0.2091 0.3763 1.0000
10.750 2.0060 0.03743 0.02990 -0.2087 0.3719 1.0000
11.000 2.0123 0.03877 0.03135 -0.2065 0.3673 1.0000
11.250 2.0139 0.04030 0.03301 -0.2037 0.3625 1.0000
11.500 2.0243 0.04140 0.03415 -0.2020 0.3580 1.0000
11.750 2.0504 0.04180 0.03444 -0.2022 0.3538 1.0000
12.000 2.0457 0.04383 0.03668 -0.1990 0.3496 1.0000
12.250 2.0456 0.04564 0.03861 -0.1964 0.3448 1.0000
12.500 2.0537 0.04693 0.03992 -0.1948 0.3403 1.0000
12.750 2.0707 0.04777 0.04071 -0.1940 0.3357 1.0000
13.000 2.0616 0.05043 0.04359 -0.1910 0.3312 1.0000
13.250 2.0631 0.05240 0.04566 -0.1890 0.3267 1.0000
13.500 2.0738 0.05367 0.04692 -0.1879 0.3227 1.0000
13.750 2.0842 0.05508 0.04837 -0.1868 0.3186 1.0000
14.000 2.0761 0.05811 0.05160 -0.1845 0.3145 1.0000
14.250 2.0763 0.06046 0.05406 -0.1829 0.3102 1.0000
14.500 2.0861 0.06192 0.05552 -0.1819 0.3064 1.0000
14.750 2.0940 0.06364 0.05728 -0.1809 0.3024 1.0000
15.000 2.0819 0.06746 0.06132 -0.1790 0.2982 1.0000
15.250 2.0800 0.07029 0.06427 -0.1778 0.2940 1.0000
15.500 2.0887 0.07191 0.06588 -0.1770 0.2899 1.0000
15.750 2.0897 0.07454 0.06861 -0.1761 0.2859 1.0000
16.000 2.0758 0.07904 0.07333 -0.1750 0.2816 1.0000
16.250 2.0725 0.08230 0.07670 -0.1742 0.2774 1.0000
16.500 2.0850 0.08350 0.07785 -0.1738 0.2732 1.0000
16.750 2.0757 0.08769 0.08222 -0.1732 0.2694 1.0000
17.000 2.0619 0.09258 0.08733 -0.1728 0.2654 1.0000
17.250 2.0579 0.09616 0.09101 -0.1726 0.2613 1.0000
17.500 2.0755 0.09656 0.09131 -0.1723 0.2566 1.0000
17.750 2.0501 0.10336 0.09840 -0.1725 0.2527 1.0000
18.000 2.0345 0.10877 0.10400 -0.1730 0.2479 1.0000
18.250 2.0429 0.11049 0.10566 -0.1729 0.2423 1.0000
18.500 2.0247 0.11645 0.11183 -0.1737 0.2379 1.0000
18.750 2.0062 0.12256 0.11813 -0.1749 0.2331 1.0000
19.000 2.0136 0.12443 0.11997 -0.1751 0.2273 1.0000
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