GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 525 AIRFOIL (goe525-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.59 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe525-il-1000000.txt Download as CSV file: xf-goe525-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.3909 0.08916 0.08689 -0.1930 0.9224 0.0251
-11.250 0.3874 0.08418 0.08188 -0.1969 0.9149 0.0274
-11.000 0.4016 0.08044 0.07809 -0.2004 0.9104 0.0276
-10.750 0.4119 0.07942 0.07706 -0.1993 0.9036 0.0278
-10.500 0.4279 0.07769 0.07530 -0.2006 0.8970 0.0280
-10.250 0.4411 0.07615 0.07372 -0.2012 0.8899 0.0284
-10.000 0.4513 0.07436 0.07191 -0.2018 0.8825 0.0287
-9.750 0.4634 0.07235 0.06985 -0.2031 0.8759 0.0293
-9.500 0.4689 0.07023 0.06773 -0.2034 0.8686 0.0304
-9.000 0.2058 0.02567 0.02260 -0.2317 0.8325 0.0287
-8.750 0.2329 0.02239 0.01910 -0.2410 0.8251 0.0290
-8.500 0.2665 0.02009 0.01661 -0.2483 0.8184 0.0294
-8.250 0.3000 0.01823 0.01449 -0.2534 0.8123 0.0298
-8.000 0.3323 0.01672 0.01277 -0.2568 0.8065 0.0300
-7.750 0.3637 0.01558 0.01145 -0.2592 0.7996 0.0303
-7.500 0.3949 0.01471 0.01038 -0.2611 0.7929 0.0305
-7.250 0.4253 0.01395 0.00950 -0.2624 0.7858 0.0308
-7.000 0.4550 0.01339 0.00878 -0.2634 0.7777 0.0311
-6.750 0.4845 0.01290 0.00819 -0.2641 0.7691 0.0313
-6.500 0.5125 0.01259 0.00773 -0.2644 0.7589 0.0315
-6.250 0.5420 0.01180 0.00684 -0.2653 0.7480 0.0319
-6.000 0.5701 0.01129 0.00625 -0.2658 0.7364 0.0324
-5.750 0.5965 0.01107 0.00595 -0.2657 0.7229 0.0330
-5.500 0.6221 0.01091 0.00569 -0.2654 0.7076 0.0334
-5.250 0.6480 0.01075 0.00544 -0.2652 0.6922 0.0339
-5.000 0.6740 0.01061 0.00520 -0.2649 0.6781 0.0343
-4.750 0.7004 0.01049 0.00499 -0.2647 0.6664 0.0347
-4.250 0.7538 0.01030 0.00464 -0.2645 0.6462 0.0356
-4.000 0.7791 0.01029 0.00453 -0.2640 0.6368 0.0360
-3.750 0.8089 0.01007 0.00426 -0.2646 0.6294 0.0367
-3.500 0.8363 0.00997 0.00410 -0.2647 0.6218 0.0376
-3.250 0.8637 0.00992 0.00401 -0.2646 0.6157 0.0385
-3.000 0.8905 0.00988 0.00393 -0.2645 0.6094 0.0397
-2.750 0.9147 0.00991 0.00390 -0.2637 0.6026 0.0408
-2.500 0.9420 0.00984 0.00380 -0.2637 0.5968 0.0421
-2.250 0.9687 0.00980 0.00374 -0.2635 0.5906 0.0441
-2.000 0.9929 0.00986 0.00373 -0.2628 0.5843 0.0462
-1.750 1.0197 0.00983 0.00370 -0.2626 0.5787 0.0506
-1.500 1.0464 0.00980 0.00369 -0.2625 0.5723 0.0626
-1.250 1.0723 0.00976 0.00374 -0.2623 0.5653 0.1113
-1.000 1.0992 0.00976 0.00381 -0.2622 0.5595 0.1422
-0.750 1.1244 0.00983 0.00388 -0.2618 0.5524 0.1601
-0.500 1.1479 0.00995 0.00399 -0.2610 0.5450 0.1786
-0.250 1.1743 0.00997 0.00408 -0.2609 0.5377 0.2171
0.000 1.1972 0.01009 0.00424 -0.2601 0.5293 0.2621
0.250 1.2219 0.01019 0.00437 -0.2595 0.5213 0.2916
0.500 1.2436 0.01038 0.00454 -0.2585 0.5115 0.3191
0.750 1.2674 0.01051 0.00470 -0.2578 0.5019 0.3474
1.000 1.2881 0.01075 0.00492 -0.2566 0.4915 0.3779
1.250 1.3108 0.01092 0.00513 -0.2558 0.4820 0.4143
1.500 1.3318 0.01118 0.00537 -0.2546 0.4731 0.4397
1.750 1.3544 0.01139 0.00558 -0.2537 0.4651 0.4597
2.000 1.3743 0.01171 0.00586 -0.2523 0.4572 0.4773
2.250 1.3969 0.01193 0.00608 -0.2515 0.4508 0.4945
2.500 1.4171 0.01224 0.00637 -0.2502 0.4434 0.5082
2.750 1.4386 0.01252 0.00663 -0.2492 0.4374 0.5208
3.000 1.4605 0.01278 0.00689 -0.2482 0.4315 0.5323
3.250 1.4803 0.01313 0.00721 -0.2469 0.4257 0.5408
3.500 1.5010 0.01345 0.00751 -0.2458 0.4207 0.5495
3.750 1.5232 0.01371 0.00777 -0.2450 0.4164 0.5570
4.000 1.5439 0.01403 0.00810 -0.2439 0.4116 0.5658
4.250 1.5629 0.01445 0.00847 -0.2425 0.4064 0.5741
4.500 1.5842 0.01474 0.00880 -0.2416 0.4027 0.5815
4.750 1.6055 0.01505 0.00911 -0.2406 0.3989 0.5886
5.000 1.6256 0.01542 0.00947 -0.2395 0.3946 0.5951
5.250 1.6441 0.01587 0.00992 -0.2382 0.3896 0.6015
5.500 1.6644 0.01624 0.01029 -0.2371 0.3853 0.6069
5.750 1.6848 0.01660 0.01065 -0.2361 0.3807 0.6120
6.000 1.7035 0.01705 0.01111 -0.2349 0.3759 0.6174
6.250 1.7205 0.01761 0.01164 -0.2334 0.3708 0.6229
6.500 1.7416 0.01796 0.01201 -0.2326 0.3677 0.6280
6.750 1.7611 0.01837 0.01246 -0.2315 0.3637 0.6328
7.000 1.7789 0.01890 0.01299 -0.2303 0.3591 0.6380
7.250 1.7946 0.01955 0.01361 -0.2287 0.3537 0.6439
7.500 1.8147 0.01996 0.01407 -0.2278 0.3506 0.6503
7.750 1.8331 0.02047 0.01461 -0.2267 0.3468 0.6570
8.000 1.8501 0.02108 0.01522 -0.2254 0.3424 0.6631
8.250 1.8652 0.02180 0.01594 -0.2239 0.3375 0.6684
8.500 1.8833 0.02235 0.01653 -0.2228 0.3340 0.6736
8.750 1.9005 0.02297 0.01717 -0.2216 0.3294 0.6790
9.000 1.9150 0.02377 0.01797 -0.2201 0.3237 0.6841
9.250 1.9298 0.02457 0.01878 -0.2187 0.3180 0.6894
9.500 1.9456 0.02531 0.01955 -0.2175 0.3126 0.6949
9.750 1.9581 0.02631 0.02053 -0.2158 0.3061 0.7003
10.000 1.9726 0.02717 0.02142 -0.2145 0.3011 0.7067
10.250 1.9864 0.02810 0.02237 -0.2131 0.2953 0.7134
10.500 1.9972 0.02927 0.02354 -0.2115 0.2890 0.7204
10.750 2.0110 0.03024 0.02455 -0.2102 0.2843 0.7286
11.000 2.0232 0.03136 0.02570 -0.2088 0.2782 0.7381
11.250 2.0317 0.03278 0.02714 -0.2070 0.2720 0.7504
11.500 2.0454 0.03382 0.02826 -0.2059 0.2671 0.7764
11.750 2.0550 0.03493 0.02958 -0.2043 0.2616 1.0000
12.000 2.0621 0.03659 0.03123 -0.2026 0.2562 1.0000
12.250 2.0745 0.03781 0.03248 -0.2015 0.2516 1.0000
12.500 2.0821 0.03949 0.03416 -0.1999 0.2462 1.0000
12.750 2.0886 0.04130 0.03597 -0.1984 0.2407 1.0000
13.000 2.0985 0.04282 0.03753 -0.1972 0.2366 1.0000
13.250 2.1053 0.04466 0.03939 -0.1958 0.2315 1.0000
13.500 2.1085 0.04692 0.04165 -0.1942 0.2261 1.0000
13.750 2.1174 0.04862 0.04340 -0.1932 0.2212 1.0000
14.000 2.1185 0.05120 0.04597 -0.1917 0.2147 1.0000
14.250 2.1219 0.05357 0.04837 -0.1904 0.2082 1.0000
14.500 2.1228 0.05628 0.05108 -0.1891 0.2012 1.0000
14.750 2.1226 0.05919 0.05401 -0.1879 0.1946 1.0000
15.000 2.1186 0.06261 0.05743 -0.1866 0.1855 1.0000
15.250 2.1127 0.06635 0.06116 -0.1854 0.1744 1.0000
15.500 2.0959 0.07158 0.06634 -0.1841 0.1585 1.0000
15.750 2.0598 0.07958 0.07422 -0.1826 0.1316 1.0000
16.000 2.0202 0.08843 0.08299 -0.1816 0.1074 1.0000
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