GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 627 AIRFOIL (goe627-il) Reynolds number: 200,000 Max Cl/Cd: 52.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe627-il-200000-n5.txt Download as CSV file: xf-goe627-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 627 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5368 0.06331 0.05933 -0.0749 0.9938 0.0271
-11.250 -0.5761 0.05437 0.05002 -0.0828 0.9868 0.0271
-11.000 -0.6039 0.04926 0.04454 -0.0836 0.9796 0.0272
-10.750 -0.6299 0.04443 0.03912 -0.0816 0.9714 0.0276
-10.500 -0.6338 0.04173 0.03613 -0.0792 0.9633 0.0280
-10.250 -0.6137 0.04014 0.03446 -0.0796 0.9596 0.0285
-10.000 -0.5878 0.03902 0.03331 -0.0808 0.9573 0.0291
-9.750 -0.5844 0.03760 0.03172 -0.0776 0.9491 0.0296
-9.500 -0.5686 0.03552 0.02936 -0.0771 0.9451 0.0302
-9.250 -0.5484 0.03325 0.02671 -0.0771 0.9424 0.0310
-9.000 -0.5453 0.03184 0.02501 -0.0731 0.9336 0.0315
-8.750 -0.5257 0.03016 0.02290 -0.0723 0.9297 0.0324
-8.500 -0.4967 0.02889 0.02161 -0.0732 0.9276 0.0331
-8.250 -0.4813 0.02802 0.02067 -0.0711 0.9210 0.0336
-8.000 -0.4589 0.02706 0.01960 -0.0703 0.9160 0.0342
-7.750 -0.4304 0.02594 0.01833 -0.0707 0.9131 0.0349
-7.500 -0.3987 0.02482 0.01704 -0.0716 0.9111 0.0358
-7.250 -0.3843 0.02414 0.01622 -0.0689 0.9031 0.0365
-7.000 -0.3569 0.02329 0.01519 -0.0688 0.8988 0.0374
-6.750 -0.3247 0.02226 0.01419 -0.0697 0.8963 0.0381
-6.500 -0.2899 0.02135 0.01326 -0.0711 0.8943 0.0389
-6.250 -0.2768 0.02082 0.01271 -0.0680 0.8844 0.0395
-6.000 -0.2440 0.02002 0.01188 -0.0689 0.8805 0.0404
-5.750 -0.2163 0.01936 0.01116 -0.0687 0.8743 0.0416
-5.500 -0.1920 0.01878 0.01051 -0.0677 0.8660 0.0426
-5.250 -0.1552 0.01794 0.00968 -0.0694 0.8619 0.0437
-5.000 -0.1393 0.01748 0.00923 -0.0668 0.8505 0.0444
-4.750 -0.1008 0.01680 0.00854 -0.0688 0.8452 0.0457
-4.500 -0.0812 0.01640 0.00811 -0.0669 0.8332 0.0468
-4.250 -0.0507 0.01593 0.00758 -0.0672 0.8238 0.0485
-4.000 -0.0191 0.01544 0.00707 -0.0678 0.8137 0.0507
-3.750 0.0080 0.01508 0.00667 -0.0675 0.8014 0.0532
-3.500 0.0394 0.01472 0.00624 -0.0679 0.7891 0.0562
-3.250 0.0710 0.01434 0.00582 -0.0685 0.7751 0.0612
-3.000 0.1007 0.01400 0.00543 -0.0686 0.7595 0.0705
-2.500 0.1474 0.01302 0.00481 -0.0667 0.7231 0.1839
-2.250 0.1676 0.01261 0.00463 -0.0652 0.7037 0.2694
-1.750 0.2060 0.01204 0.00436 -0.0616 0.6671 0.4012
-1.500 0.2197 0.01164 0.00429 -0.0585 0.6504 0.5048
-1.250 0.2324 0.01127 0.00430 -0.0551 0.6340 0.6213
-1.000 0.2517 0.01108 0.00443 -0.0528 0.6170 0.7295
-0.750 0.2847 0.01117 0.00465 -0.0531 0.5973 0.8146
-0.500 0.3237 0.01144 0.00488 -0.0548 0.5764 0.8657
-0.250 0.3600 0.01172 0.00503 -0.0562 0.5563 0.8894
0.000 0.3906 0.01197 0.00513 -0.0565 0.5362 0.9053
0.250 0.4276 0.01229 0.00527 -0.0582 0.5141 0.9171
0.500 0.4594 0.01257 0.00538 -0.0589 0.4929 0.9269
0.750 0.4903 0.01287 0.00552 -0.0595 0.4712 0.9371
1.000 0.5256 0.01323 0.00571 -0.0610 0.4512 0.9454
1.250 0.5571 0.01357 0.00591 -0.0617 0.4337 0.9565
1.500 0.5974 0.01392 0.00611 -0.0643 0.4166 0.9636
1.750 0.6313 0.01424 0.00629 -0.0657 0.4018 0.9719
2.000 0.6675 0.01453 0.00645 -0.0677 0.3874 0.9783
2.250 0.6997 0.01478 0.00659 -0.0688 0.3741 0.9841
2.500 0.7332 0.01501 0.00671 -0.0703 0.3612 0.9886
2.750 0.7645 0.01527 0.00687 -0.0714 0.3506 0.9935
3.000 0.7981 0.01549 0.00700 -0.0730 0.3402 0.9976
3.250 0.8247 0.01569 0.00714 -0.0731 0.3320 1.0000
3.500 0.8351 0.01586 0.00726 -0.0699 0.3254 1.0000
3.750 0.8437 0.01607 0.00740 -0.0663 0.3197 1.0000
4.000 0.8537 0.01620 0.00752 -0.0630 0.3140 1.0000
4.250 0.8618 0.01636 0.00765 -0.0592 0.3084 1.0000
4.500 0.8693 0.01658 0.00779 -0.0554 0.3033 1.0000
4.750 0.8812 0.01675 0.00796 -0.0525 0.2984 1.0000
5.000 0.8931 0.01695 0.00814 -0.0495 0.2933 1.0000
5.250 0.9048 0.01720 0.00834 -0.0466 0.2889 1.0000
5.500 0.9177 0.01748 0.00858 -0.0439 0.2852 1.0000
5.750 0.9333 0.01771 0.00882 -0.0418 0.2812 1.0000
6.000 0.9485 0.01798 0.00908 -0.0395 0.2774 1.0000
6.250 0.9633 0.01828 0.00935 -0.0373 0.2737 1.0000
6.500 0.9778 0.01862 0.00966 -0.0351 0.2703 1.0000
6.750 0.9942 0.01894 0.00997 -0.0332 0.2671 1.0000
7.000 1.0112 0.01923 0.01030 -0.0315 0.2635 1.0000
7.250 1.0279 0.01957 0.01065 -0.0297 0.2602 1.0000
7.500 1.0444 0.01993 0.01100 -0.0280 0.2574 1.0000
7.750 1.0606 0.02033 0.01138 -0.0262 0.2548 1.0000
8.000 1.0777 0.02077 0.01179 -0.0247 0.2523 1.0000
8.250 1.0952 0.02112 0.01221 -0.0232 0.2494 1.0000
8.500 1.1119 0.02149 0.01263 -0.0216 0.2462 1.0000
8.750 1.1271 0.02190 0.01307 -0.0198 0.2423 1.0000
9.000 1.1420 0.02237 0.01352 -0.0181 0.2389 1.0000
9.250 1.1575 0.02289 0.01400 -0.0165 0.2360 1.0000
9.500 1.1738 0.02332 0.01453 -0.0151 0.2331 1.0000
9.750 1.1896 0.02378 0.01507 -0.0136 0.2299 1.0000
10.000 1.2042 0.02429 0.01562 -0.0120 0.2267 1.0000
10.250 1.2186 0.02484 0.01619 -0.0104 0.2238 1.0000
10.500 1.2329 0.02544 0.01678 -0.0089 0.2212 1.0000
10.750 1.2478 0.02603 0.01743 -0.0075 0.2186 1.0000
11.000 1.2630 0.02661 0.01812 -0.0062 0.2161 1.0000
11.250 1.2764 0.02725 0.01884 -0.0047 0.2130 1.0000
11.500 1.2897 0.02792 0.01958 -0.0033 0.2103 1.0000
11.750 1.3020 0.02865 0.02035 -0.0019 0.2076 1.0000
12.000 1.3147 0.02943 0.02113 -0.0005 0.2053 1.0000
12.250 1.3274 0.03021 0.02201 0.0007 0.2029 1.0000
12.500 1.3394 0.03104 0.02297 0.0020 0.2001 1.0000
12.750 1.3504 0.03193 0.02397 0.0033 0.1972 1.0000
13.000 1.3608 0.03288 0.02500 0.0046 0.1945 1.0000
13.250 1.3702 0.03390 0.02606 0.0058 0.1918 1.0000
13.500 1.3792 0.03499 0.02717 0.0071 0.1893 1.0000
13.750 1.3882 0.03615 0.02850 0.0081 0.1864 1.0000
14.000 1.3962 0.03741 0.02990 0.0092 0.1831 1.0000
14.250 1.4026 0.03878 0.03136 0.0102 0.1799 1.0000
14.500 1.4079 0.04027 0.03290 0.0112 0.1769 1.0000
14.750 1.4125 0.04191 0.03464 0.0120 0.1733 1.0000
15.000 1.4160 0.04375 0.03663 0.0127 0.1686 1.0000
15.250 1.4176 0.04578 0.03873 0.0133 0.1645 1.0000
15.500 1.4181 0.04800 0.04101 0.0138 0.1605 1.0000
15.750 1.4190 0.05033 0.04348 0.0141 0.1558 1.0000
16.000 1.4165 0.05305 0.04627 0.0142 0.1512 1.0000
16.250 1.4137 0.05591 0.04921 0.0142 0.1474 1.0000
16.500 1.4111 0.05887 0.05230 0.0140 0.1431 1.0000
16.750 1.4034 0.06248 0.05598 0.0136 0.1385 1.0000
17.000 1.3974 0.06598 0.05956 0.0131 0.1356 1.0000
17.250 1.3905 0.06974 0.06346 0.0124 0.1319 1.0000
17.500 1.3799 0.07404 0.06785 0.0114 0.1282 1.0000
17.750 1.3664 0.07880 0.07266 0.0102 0.1250 1.0000
18.000 1.3554 0.08336 0.07735 0.0089 0.1219 1.0000
18.250 1.3420 0.08836 0.08247 0.0074 0.1189 1.0000
18.500 1.3268 0.09365 0.08784 0.0057 0.1160 1.0000
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