GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 200,000 Max Cl/Cd: 58.94 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe513-il-200000.txt Download as CSV file: xf-goe513-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2180 0.09736 0.09399 -0.0648 0.9701 0.0923
-9.250 -0.1946 0.09449 0.09111 -0.0677 0.9681 0.0951
-9.000 -0.2517 0.08385 0.08050 -0.0835 0.9549 0.1017
-8.750 -0.2082 0.08286 0.07952 -0.0809 0.9543 0.1030
-8.500 -0.1901 0.08112 0.07779 -0.0801 0.9473 0.1046
-8.250 -0.1778 0.07752 0.07418 -0.0839 0.9417 0.1077
-8.000 -0.2476 0.06958 0.06609 -0.0877 0.9243 0.1146
-7.750 -0.4595 0.03986 0.03382 -0.0665 0.8943 0.0626
-7.500 -0.4349 0.03790 0.03155 -0.0661 0.8911 0.0621
-7.250 -0.4292 0.03607 0.02951 -0.0623 0.8828 0.0620
-7.000 -0.4089 0.03392 0.02712 -0.0611 0.8777 0.0618
-6.750 -0.3799 0.03171 0.02465 -0.0613 0.8749 0.0615
-6.500 -0.3461 0.02972 0.02240 -0.0623 0.8731 0.0614
-6.250 -0.3419 0.02893 0.02144 -0.0576 0.8622 0.0616
-6.000 -0.3066 0.02735 0.01963 -0.0585 0.8594 0.0617
-5.750 -0.2669 0.02595 0.01800 -0.0602 0.8575 0.0622
-5.500 -0.2489 0.02472 0.01674 -0.0582 0.8490 0.0630
-5.250 -0.2121 0.02338 0.01541 -0.0596 0.8452 0.0644
-5.000 -0.1686 0.02209 0.01411 -0.0621 0.8428 0.0658
-4.750 -0.1197 0.02080 0.01279 -0.0657 0.8408 0.0673
-4.500 -0.0966 0.02012 0.01207 -0.0643 0.8320 0.0685
-4.250 -0.0544 0.01916 0.01106 -0.0665 0.8268 0.0701
-4.000 -0.0011 0.01785 0.00987 -0.0714 0.8232 0.0739
-3.750 0.0218 0.01732 0.00934 -0.0699 0.8116 0.0769
-3.500 0.0774 0.01633 0.00834 -0.0751 0.8051 0.0827
-3.250 0.1037 0.01587 0.00784 -0.0744 0.7913 0.0893
-3.000 0.1408 0.01500 0.00714 -0.0760 0.7775 0.1175
-2.750 0.1714 0.01490 0.00734 -0.0761 0.7620 0.2358
-2.500 0.1964 0.01512 0.00738 -0.0750 0.7445 0.2556
-2.250 0.2197 0.01523 0.00740 -0.0737 0.7256 0.2683
-2.000 0.2404 0.01534 0.00738 -0.0719 0.7057 0.2796
-1.750 0.2579 0.01551 0.00741 -0.0694 0.6862 0.2906
-1.500 0.2771 0.01551 0.00735 -0.0674 0.6671 0.2994
-1.250 0.2940 0.01559 0.00729 -0.0649 0.6487 0.3082
-1.000 0.3128 0.01555 0.00715 -0.0628 0.6310 0.3157
-0.750 0.3289 0.01561 0.00711 -0.0602 0.6143 0.3256
-0.500 0.3485 0.01558 0.00698 -0.0584 0.5991 0.3344
-0.250 0.3715 0.01560 0.00687 -0.0573 0.5864 0.3415
0.000 0.3930 0.01564 0.00680 -0.0559 0.5748 0.3466
0.250 0.4208 0.01561 0.00668 -0.0559 0.5644 0.3514
0.500 0.4460 0.01563 0.00666 -0.0554 0.5544 0.3572
0.750 0.4726 0.01571 0.00665 -0.0552 0.5455 0.3634
1.000 0.4975 0.01573 0.00665 -0.0546 0.5368 0.3693
1.250 0.5264 0.01581 0.00667 -0.0549 0.5289 0.3769
1.500 0.5464 0.01586 0.00673 -0.0533 0.5209 0.3849
1.750 0.5743 0.01591 0.00675 -0.0534 0.5134 0.3953
2.000 0.5894 0.01590 0.00683 -0.0508 0.5058 0.4070
2.250 0.6053 0.01587 0.00686 -0.0484 0.4986 0.4253
2.500 0.6224 0.01552 0.00686 -0.0463 0.4923 0.5221
2.750 0.8910 0.01740 0.00959 -0.0956 0.4688 0.9752
3.000 0.9563 0.01765 0.00972 -0.1035 0.4581 0.9880
3.250 1.0182 0.01764 0.00965 -0.1108 0.4467 0.9986
3.500 1.0406 0.01776 0.00969 -0.1100 0.4389 1.0000
3.750 1.0531 0.01793 0.00985 -0.1072 0.4314 1.0000
4.000 1.0639 0.01807 0.00998 -0.1040 0.4238 1.0000
4.250 1.0781 0.01829 0.01010 -0.1015 0.4168 1.0000
4.500 1.0857 0.01843 0.01028 -0.0976 0.4086 1.0000
4.750 1.0976 0.01863 0.01039 -0.0947 0.4016 1.0000
5.000 1.1051 0.01882 0.01061 -0.0908 0.3936 1.0000
5.250 1.1124 0.01901 0.01074 -0.0869 0.3862 1.0000
5.500 1.1189 0.01923 0.01092 -0.0829 0.3789 1.0000
5.750 1.1231 0.01942 0.01110 -0.0784 0.3712 1.0000
6.000 1.1331 0.01971 0.01128 -0.0752 0.3644 1.0000
6.250 1.1382 0.01994 0.01157 -0.0709 0.3569 1.0000
6.500 1.1484 0.02026 0.01179 -0.0678 0.3503 1.0000
6.750 1.1594 0.02061 0.01213 -0.0648 0.3439 1.0000
7.000 1.1688 0.02093 0.01247 -0.0616 0.3376 1.0000
7.250 1.1846 0.02134 0.01275 -0.0596 0.3322 1.0000
7.500 1.1962 0.02174 0.01318 -0.0569 0.3268 1.0000
7.750 1.2075 0.02211 0.01358 -0.0541 0.3216 1.0000
8.000 1.2226 0.02253 0.01392 -0.0521 0.3168 1.0000
8.250 1.2392 0.02300 0.01436 -0.0505 0.3122 1.0000
8.500 1.2498 0.02343 0.01486 -0.0477 0.3078 1.0000
8.750 1.2634 0.02387 0.01530 -0.0455 0.3037 1.0000
9.000 1.2815 0.02433 0.01571 -0.0442 0.3001 1.0000
9.250 1.3029 0.02488 0.01621 -0.0435 0.2964 1.0000
9.500 1.3130 0.02539 0.01683 -0.0408 0.2932 1.0000
9.750 1.3252 0.02590 0.01739 -0.0385 0.2897 1.0000
10.000 1.3401 0.02639 0.01789 -0.0367 0.2865 1.0000
10.250 1.3594 0.02690 0.01835 -0.0357 0.2834 1.0000
10.500 1.3849 0.02752 0.01893 -0.0358 0.2804 1.0000
10.750 1.3924 0.02816 0.01971 -0.0329 0.2781 1.0000
11.000 1.4033 0.02881 0.02046 -0.0307 0.2756 1.0000
11.250 1.4155 0.02943 0.02115 -0.0287 0.2728 1.0000
11.500 1.4303 0.03001 0.02175 -0.0271 0.2702 1.0000
11.750 1.4499 0.03058 0.02231 -0.0264 0.2676 1.0000
12.000 1.4836 0.03127 0.02292 -0.0279 0.2646 1.0000
12.250 1.4846 0.03212 0.02394 -0.0243 0.2629 1.0000
12.500 1.4891 0.03301 0.02498 -0.0215 0.2609 1.0000
12.750 1.4960 0.03391 0.02600 -0.0191 0.2587 1.0000
13.000 1.5047 0.03475 0.02693 -0.0170 0.2564 1.0000
13.250 1.5171 0.03548 0.02770 -0.0154 0.2540 1.0000
13.500 1.5375 0.03604 0.02823 -0.0149 0.2514 1.0000
13.750 1.5649 0.03680 0.02896 -0.0155 0.2483 1.0000
14.000 1.5550 0.03810 0.03047 -0.0113 0.2464 1.0000
14.250 1.5495 0.03950 0.03203 -0.0079 0.2443 1.0000
14.500 1.5466 0.04084 0.03351 -0.0051 0.2418 1.0000
14.750 1.5502 0.04183 0.03456 -0.0030 0.2387 1.0000
15.000 1.5676 0.04230 0.03500 -0.0023 0.2357 1.0000
15.250 1.5984 0.04280 0.03541 -0.0031 0.2326 1.0000
15.500 1.5783 0.04493 0.03778 0.0009 0.2308 1.0000
15.750 1.5644 0.04720 0.04026 0.0039 0.2289 1.0000
16.000 1.5521 0.04949 0.04271 0.0064 0.2264 1.0000
16.250 1.5487 0.05138 0.04472 0.0080 0.2240 1.0000
16.500 1.5584 0.05236 0.04571 0.0089 0.2213 1.0000
16.750 1.5923 0.05184 0.04507 0.0085 0.2182 1.0000
17.000 1.5807 0.05450 0.04789 0.0103 0.2160 1.0000
17.250 1.5517 0.05863 0.05228 0.0124 0.2143 1.0000
17.500 1.5206 0.06344 0.05732 0.0139 0.2123 1.0000
17.750 1.4887 0.06880 0.06290 0.0147 0.2101 1.0000
18.000 1.4754 0.07244 0.06665 0.0149 0.2075 1.0000
18.250 1.5358 0.06805 0.06205 0.0153 0.2039 1.0000
18.500 1.5324 0.07062 0.06469 0.0156 0.2010 1.0000
18.750 1.4555 0.08196 0.07641 0.0148 0.1995 1.0000
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