GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 525 AIRFOIL (goe525-il) Reynolds number: 200,000 Max Cl/Cd: 71.49 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe525-il-200000-n5.txt Download as CSV file: xf-goe525-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.2989 0.09798 0.09367 -0.1601 0.8973 0.0465
-10.250 0.2946 0.09595 0.09166 -0.1602 0.8905 0.0467
-10.000 0.3017 0.09315 0.08887 -0.1616 0.8854 0.0470
-9.750 0.3305 0.09075 0.08645 -0.1623 0.8833 0.0481
-9.500 0.3513 0.08802 0.08369 -0.1655 0.8809 0.0494
-9.250 0.3542 0.08631 0.08200 -0.1647 0.8741 0.0505
-9.000 0.3591 0.08383 0.07951 -0.1662 0.8679 0.0522
-8.750 0.3576 0.07699 0.07258 -0.1720 0.8637 0.0411
-8.500 0.3494 0.07529 0.07091 -0.1693 0.8541 0.0411
-8.250 0.3608 0.07211 0.06770 -0.1718 0.8490 0.0411
-8.000 0.3675 0.07007 0.06566 -0.1716 0.8421 0.0410
-7.750 0.3739 0.06822 0.06380 -0.1711 0.8338 0.0408
-7.500 0.3847 0.06582 0.06136 -0.1722 0.8266 0.0404
-7.250 0.3819 0.06389 0.05943 -0.1706 0.8163 0.0402
-7.000 0.3779 0.06193 0.05747 -0.1690 0.8064 0.0399
-6.750 0.3738 0.05951 0.05502 -0.1681 0.7971 0.0397
-6.500 0.3557 0.05783 0.05337 -0.1640 0.7853 0.0396
-6.000 0.4090 0.02425 0.01812 -0.2280 0.7640 0.0398
-5.750 0.4584 0.02222 0.01564 -0.2346 0.7574 0.0403
-5.500 0.4962 0.02096 0.01404 -0.2378 0.7488 0.0409
-5.250 0.5370 0.01996 0.01283 -0.2411 0.7414 0.0415
-5.000 0.5662 0.01941 0.01222 -0.2419 0.7318 0.0424
-4.750 0.6019 0.01884 0.01151 -0.2438 0.7233 0.0435
-4.500 0.6335 0.01833 0.01085 -0.2449 0.7134 0.0444
-4.250 0.6666 0.01784 0.01020 -0.2462 0.7043 0.0452
-4.000 0.6987 0.01743 0.00965 -0.2472 0.6950 0.0461
-3.750 0.7300 0.01710 0.00920 -0.2481 0.6859 0.0470
-3.500 0.7620 0.01680 0.00884 -0.2492 0.6768 0.0481
-3.250 0.7923 0.01660 0.00857 -0.2499 0.6678 0.0494
-3.000 0.8230 0.01645 0.00831 -0.2506 0.6593 0.0516
-2.750 0.8534 0.01632 0.00810 -0.2513 0.6516 0.0540
-2.500 0.8830 0.01623 0.00794 -0.2519 0.6434 0.0568
-2.000 0.9417 0.01612 0.00767 -0.2529 0.6279 0.0656
-1.750 0.9725 0.01608 0.00756 -0.2537 0.6207 0.0762
-1.500 1.0007 0.01602 0.00758 -0.2540 0.6138 0.1017
-1.250 1.0279 0.01604 0.00763 -0.2542 0.6065 0.1386
-1.000 1.0560 0.01612 0.00766 -0.2544 0.5998 0.1645
-0.750 1.0802 0.01617 0.00778 -0.2539 0.5923 0.1933
-0.500 1.1067 0.01624 0.00795 -0.2539 0.5851 0.2488
-0.250 1.1317 0.01635 0.00814 -0.2536 0.5785 0.3046
0.000 1.1545 0.01649 0.00835 -0.2528 0.5711 0.3422
0.250 1.1786 0.01670 0.00853 -0.2522 0.5642 0.3740
0.500 1.2001 0.01690 0.00878 -0.2511 0.5569 0.3990
0.750 1.2217 0.01714 0.00901 -0.2500 0.5495 0.4210
1.000 1.2436 0.01741 0.00925 -0.2490 0.5427 0.4432
1.250 1.2640 0.01768 0.00953 -0.2477 0.5350 0.4626
1.500 1.2846 0.01799 0.00979 -0.2464 0.5279 0.4798
1.750 1.3044 0.01830 0.01010 -0.2451 0.5203 0.4973
2.000 1.3239 0.01865 0.01041 -0.2437 0.5128 0.5149
2.250 1.3435 0.01901 0.01074 -0.2423 0.5059 0.5314
2.500 1.3620 0.01939 0.01111 -0.2408 0.4981 0.5439
2.750 1.3808 0.01981 0.01145 -0.2393 0.4912 0.5567
3.000 1.3997 0.02021 0.01185 -0.2379 0.4839 0.5704
3.250 1.4173 0.02066 0.01227 -0.2363 0.4768 0.5812
3.500 1.4362 0.02112 0.01269 -0.2350 0.4702 0.5922
3.750 1.4542 0.02158 0.01314 -0.2335 0.4632 0.6001
4.000 1.4720 0.02211 0.01358 -0.2321 0.4569 0.6094
4.250 1.4907 0.02258 0.01408 -0.2308 0.4509 0.6164
4.500 1.5089 0.02310 0.01458 -0.2295 0.4449 0.6242
4.750 1.5270 0.02366 0.01507 -0.2282 0.4395 0.6312
5.000 1.5455 0.02418 0.01563 -0.2270 0.4343 0.6384
5.250 1.5634 0.02475 0.01619 -0.2257 0.4287 0.6464
5.500 1.5807 0.02535 0.01676 -0.2244 0.4236 0.6525
5.750 1.5988 0.02595 0.01735 -0.2232 0.4190 0.6600
6.000 1.6164 0.02654 0.01800 -0.2219 0.4143 0.6680
6.250 1.6335 0.02718 0.01865 -0.2207 0.4096 0.6779
6.500 1.6505 0.02784 0.01930 -0.2194 0.4053 0.6870
6.750 1.6678 0.02851 0.01999 -0.2182 0.4013 0.6954
7.000 1.6841 0.02920 0.02074 -0.2169 0.3967 0.7016
7.250 1.6997 0.02993 0.02150 -0.2155 0.3920 0.7084
7.500 1.7149 0.03073 0.02228 -0.2141 0.3876 0.7155
7.750 1.7302 0.03151 0.02310 -0.2128 0.3835 0.7221
8.000 1.7451 0.03233 0.02399 -0.2115 0.3789 0.7296
8.250 1.7592 0.03319 0.02491 -0.2100 0.3745 0.7373
8.500 1.7731 0.03410 0.02583 -0.2086 0.3705 0.7464
8.750 1.7876 0.03498 0.02675 -0.2073 0.3668 0.7561
9.000 1.8013 0.03592 0.02781 -0.2060 0.3626 0.7678
9.250 1.8139 0.03691 0.02891 -0.2045 0.3584 0.7852
9.500 1.8231 0.03783 0.02995 -0.2026 0.3541 0.8927
9.750 1.8338 0.03901 0.03114 -0.2010 0.3498 1.0000
10.000 1.8445 0.04032 0.03254 -0.1996 0.3446 1.0000
10.250 1.8540 0.04173 0.03399 -0.1981 0.3394 1.0000
10.500 1.8633 0.04318 0.03542 -0.1967 0.3348 1.0000
10.750 1.8731 0.04465 0.03697 -0.1954 0.3302 1.0000
11.000 1.8822 0.04620 0.03860 -0.1940 0.3255 1.0000
11.250 1.8909 0.04781 0.04024 -0.1927 0.3212 1.0000
11.500 1.8997 0.04942 0.04185 -0.1914 0.3175 1.0000
11.750 1.9091 0.05107 0.04361 -0.1903 0.3136 1.0000
12.000 1.9172 0.05284 0.04548 -0.1891 0.3097 1.0000
12.250 1.9252 0.05464 0.04733 -0.1880 0.3059 1.0000
12.500 1.9326 0.05650 0.04922 -0.1868 0.3025 1.0000
12.750 1.9398 0.05844 0.05124 -0.1858 0.2988 1.0000
13.000 1.9446 0.06069 0.05361 -0.1847 0.2943 1.0000
13.250 1.9482 0.06307 0.05604 -0.1836 0.2895 1.0000
13.750 1.9526 0.06832 0.06142 -0.1816 0.2796 1.0000
14.000 1.9530 0.07123 0.06442 -0.1807 0.2741 1.0000
14.250 1.9540 0.07405 0.06723 -0.1798 0.2692 1.0000
14.500 1.9544 0.07713 0.07046 -0.1792 0.2644 1.0000
14.750 1.9552 0.08016 0.07359 -0.1786 0.2599 1.0000
15.000 1.9557 0.08322 0.07669 -0.1780 0.2556 1.0000
15.250 1.9563 0.08630 0.07985 -0.1776 0.2516 1.0000
15.500 1.9558 0.08963 0.08332 -0.1773 0.2473 1.0000
15.750 1.9537 0.09317 0.08695 -0.1770 0.2427 1.0000
16.000 1.9525 0.09652 0.09033 -0.1768 0.2382 1.0000
16.250 1.9500 0.10022 0.09418 -0.1768 0.2339 1.0000
16.500 1.9466 0.10406 0.09814 -0.1769 0.2294 1.0000
16.750 1.9438 0.10777 0.10192 -0.1770 0.2249 1.0000
17.000 1.9415 0.11141 0.10564 -0.1773 0.2209 1.0000
17.250 1.9368 0.11553 0.10991 -0.1778 0.2164 1.0000
17.500 1.9316 0.11967 0.11415 -0.1783 0.2114 1.0000
17.750 1.9261 0.12385 0.11839 -0.1790 0.2062 1.0000
18.000 1.9184 0.12850 0.12319 -0.1800 0.2006 1.0000
18.250 1.9106 0.13310 0.12785 -0.1810 0.1943 1.0000
18.500 1.9026 0.13781 0.13269 -0.1823 0.1879 1.0000
18.750 1.8918 0.14296 0.13790 -0.1838 0.1797 1.0000
19.000 1.8810 0.14816 0.14321 -0.1855 0.1703 1.0000
19.250 1.8683 0.15365 0.14874 -0.1875 0.1581 1.0000
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Polar data table (+)
Polar graphs
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