GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 511 AIRFOIL (goe511-il) Reynolds number: 500,000 Max Cl/Cd: 71.83 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe511-il-500000.txt Download as CSV file: xf-goe511-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 511 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
------ -------- --------- --------- -------- -------- --------
-11.000 0.1224 0.09810 0.09556 -0.1211 0.9478 0.0342
-10.750 0.1372 0.09474 0.09219 -0.1242 0.9458 0.0352
-10.500 0.1259 0.08748 0.08492 -0.1327 0.9437 0.0370
-10.250 0.1565 0.08485 0.08228 -0.1351 0.9425 0.0374
-10.000 0.1860 0.08182 0.07923 -0.1391 0.9411 0.0378
-9.750 0.2459 0.06160 0.05909 -0.1512 0.9265 0.0419
-9.500 0.2755 0.05865 0.05612 -0.1533 0.9240 0.0422
-9.250 0.2797 0.05723 0.05472 -0.1512 0.9155 0.0425
-9.000 0.2979 0.05450 0.05196 -0.1534 0.9095 0.0430
-8.750 0.3067 0.05225 0.04971 -0.1539 0.9008 0.0437
-8.500 0.3145 0.04933 0.04676 -0.1556 0.8921 0.0450
-8.250 0.2671 0.05866 0.05602 -0.1632 0.9043 0.0439
-8.000 0.2603 0.05619 0.05353 -0.1629 0.8925 0.0445
-7.750 0.2346 0.05354 0.05085 -0.1594 0.8785 0.0464
-7.500 0.1927 0.04715 0.04431 -0.1569 0.8626 0.0479
-7.250 0.1989 0.04587 0.04298 -0.1545 0.8460 0.0481
-7.000 0.2115 0.04462 0.04163 -0.1533 0.8226 0.0486
-6.750 0.2228 0.04291 0.03970 -0.1522 0.7832 0.0491
-6.500 0.1660 0.03280 0.02885 -0.1448 0.7552 0.0541
-6.250 0.1763 0.03218 0.02809 -0.1418 0.7258 0.0544
-6.000 0.1833 0.03173 0.02750 -0.1381 0.7026 0.0548
-5.750 0.1867 0.03099 0.02662 -0.1339 0.6823 0.0553
-5.500 0.1865 0.03028 0.02578 -0.1287 0.6625 0.0561
-5.250 0.1804 0.02890 0.02419 -0.1226 0.6434 0.0574
-5.000 0.1181 0.01919 0.01261 -0.1049 0.6385 0.0422
-4.750 0.1259 0.01873 0.01192 -0.1006 0.6191 0.0420
-4.500 0.1351 0.01811 0.01110 -0.0967 0.6008 0.0421
-4.250 0.1469 0.01741 0.01021 -0.0933 0.5854 0.0422
-4.000 0.1619 0.01682 0.00947 -0.0906 0.5725 0.0424
-3.750 0.1783 0.01635 0.00887 -0.0881 0.5618 0.0426
-3.500 0.1972 0.01598 0.00843 -0.0862 0.5522 0.0432
-3.250 0.2161 0.01577 0.00813 -0.0843 0.5436 0.0439
-3.000 0.2369 0.01547 0.00776 -0.0827 0.5361 0.0443
-2.750 0.2572 0.01523 0.00741 -0.0810 0.5287 0.0448
-2.500 0.2786 0.01500 0.00710 -0.0796 0.5221 0.0453
-2.250 0.3000 0.01477 0.00681 -0.0781 0.5154 0.0458
-2.000 0.3206 0.01464 0.00657 -0.0764 0.5084 0.0463
-1.750 0.3424 0.01453 0.00640 -0.0750 0.5025 0.0470
-1.500 0.3640 0.01437 0.00621 -0.0736 0.4966 0.0474
-1.250 0.3840 0.01406 0.00589 -0.0720 0.4907 0.0484
-1.000 0.4045 0.01396 0.00576 -0.0704 0.4852 0.0493
-0.750 0.4251 0.01386 0.00568 -0.0688 0.4797 0.0507
-0.500 0.4451 0.01380 0.00559 -0.0672 0.4740 0.0522
-0.250 0.4647 0.01382 0.00554 -0.0654 0.4680 0.0532
0.000 0.4844 0.01364 0.00540 -0.0637 0.4628 0.0552
0.250 0.5041 0.01358 0.00534 -0.0620 0.4569 0.0573
0.500 0.5230 0.01361 0.00531 -0.0601 0.4510 0.0595
0.750 0.5422 0.01357 0.00527 -0.0583 0.4454 0.0637
1.000 0.5611 0.01354 0.00527 -0.0565 0.4393 0.0705
1.250 0.5765 0.01342 0.00528 -0.0540 0.4334 0.1180
1.500 0.5942 0.01341 0.00552 -0.0521 0.4280 0.2113
1.750 0.6150 0.01352 0.00565 -0.0507 0.4223 0.2284
2.000 0.6348 0.01371 0.00578 -0.0492 0.4164 0.2399
2.250 0.6531 0.01387 0.00592 -0.0474 0.4110 0.2489
2.500 0.6742 0.01400 0.00605 -0.0462 0.4060 0.2575
2.750 0.6932 0.01413 0.00618 -0.0446 0.4009 0.2661
3.000 0.7120 0.01434 0.00633 -0.0430 0.3959 0.2734
3.250 0.7323 0.01449 0.00647 -0.0417 0.3917 0.2802
3.500 0.7526 0.01461 0.00663 -0.0404 0.3873 0.2890
3.750 0.7722 0.01479 0.00678 -0.0390 0.3832 0.2964
4.000 0.7901 0.01498 0.00696 -0.0373 0.3789 0.3043
4.250 0.8101 0.01518 0.00714 -0.0360 0.3752 0.3117
4.500 0.8304 0.01530 0.00731 -0.0348 0.3718 0.3208
4.750 1.0242 0.01491 0.00850 -0.0717 0.3633 0.9769
5.000 1.1303 0.01578 0.00923 -0.0888 0.3580 1.0000
5.250 1.1473 0.01598 0.00943 -0.0870 0.3559 1.0000
5.500 1.1641 0.01621 0.00965 -0.0851 0.3535 1.0000
5.750 1.1809 0.01644 0.00987 -0.0833 0.3510 1.0000
6.000 1.1978 0.01670 0.01011 -0.0816 0.3486 1.0000
6.250 1.2137 0.01700 0.01036 -0.0797 0.3456 1.0000
6.500 1.2319 0.01735 0.01064 -0.0783 0.3426 1.0000
6.750 1.2492 0.01761 0.01092 -0.0767 0.3407 1.0000
7.000 1.2643 0.01788 0.01122 -0.0747 0.3381 1.0000
7.250 1.2818 0.01815 0.01151 -0.0732 0.3362 1.0000
7.500 1.2977 0.01845 0.01181 -0.0715 0.3335 1.0000
7.750 1.3141 0.01878 0.01213 -0.0698 0.3313 1.0000
8.000 1.3306 0.01914 0.01247 -0.0683 0.3291 1.0000
8.250 1.3484 0.01953 0.01281 -0.0670 0.3263 1.0000
8.500 1.3662 0.01988 0.01317 -0.0657 0.3241 1.0000
8.750 1.3823 0.02022 0.01356 -0.0641 0.3225 1.0000
9.000 1.3978 0.02059 0.01397 -0.0625 0.3206 1.0000
9.250 1.4128 0.02098 0.01440 -0.0609 0.3184 1.0000
9.500 1.4284 0.02138 0.01482 -0.0594 0.3162 1.0000
9.750 1.4442 0.02180 0.01524 -0.0579 0.3143 1.0000
10.000 1.4599 0.02225 0.01569 -0.0565 0.3123 1.0000
10.250 1.4769 0.02271 0.01613 -0.0554 0.3099 1.0000
10.500 1.4942 0.02316 0.01659 -0.0543 0.3076 1.0000
10.750 1.5087 0.02364 0.01714 -0.0528 0.3063 1.0000
11.000 1.5217 0.02418 0.01774 -0.0512 0.3044 1.0000
11.250 1.5354 0.02473 0.01835 -0.0497 0.3025 1.0000
11.500 1.5492 0.02529 0.01895 -0.0483 0.3004 1.0000
11.750 1.5630 0.02587 0.01957 -0.0469 0.2986 1.0000
12.000 1.5758 0.02650 0.02023 -0.0455 0.2965 1.0000
12.250 1.5903 0.02711 0.02084 -0.0443 0.2943 1.0000
12.500 1.6073 0.02766 0.02138 -0.0435 0.2916 1.0000
12.750 1.6166 0.02849 0.02231 -0.0418 0.2900 1.0000
13.000 1.6264 0.02934 0.02325 -0.0402 0.2879 1.0000
13.250 1.6351 0.03027 0.02426 -0.0387 0.2852 1.0000
13.500 1.6446 0.03121 0.02524 -0.0373 0.2826 1.0000
13.750 1.6520 0.03230 0.02634 -0.0357 0.2791 1.0000
14.000 1.6614 0.03332 0.02735 -0.0345 0.2755 1.0000
14.250 1.6671 0.03465 0.02881 -0.0331 0.2728 1.0000
14.500 1.6743 0.03593 0.03019 -0.0319 0.2697 1.0000
14.750 1.6807 0.03731 0.03162 -0.0307 0.2664 1.0000
15.000 1.6841 0.03893 0.03324 -0.0295 0.2623 1.0000
15.250 1.6896 0.04045 0.03483 -0.0284 0.2591 1.0000
15.500 1.6938 0.04219 0.03669 -0.0275 0.2549 1.0000
15.750 1.6959 0.04413 0.03868 -0.0265 0.2503 1.0000
16.000 1.6931 0.04652 0.04106 -0.0254 0.2452 1.0000
16.250 1.6968 0.04844 0.04311 -0.0247 0.2409 1.0000
16.500 1.6931 0.05109 0.04580 -0.0239 0.2348 1.0000
16.750 1.6872 0.05401 0.04876 -0.0231 0.2292 1.0000
17.000 1.6822 0.05694 0.05177 -0.0225 0.2226 1.0000
17.250 1.6695 0.06071 0.05556 -0.0218 0.2160 1.0000
17.500 1.6610 0.06413 0.05904 -0.0214 0.2092 1.0000
17.750 1.6418 0.06877 0.06370 -0.0209 0.2020 1.0000
18.000 1.6290 0.07279 0.06777 -0.0207 0.1956 1.0000
18.250 1.6074 0.07783 0.07280 -0.0205 0.1895 1.0000
18.500 1.5973 0.08163 0.07668 -0.0205 0.1848 1.0000
18.750 1.5820 0.08609 0.08116 -0.0206 0.1802 1.0000
19.000 1.5679 0.09041 0.08549 -0.0207 0.1758 1.0000
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