GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 500,000 Max Cl/Cd: 65.47 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe599-il-500000-n5.txt Download as CSV file: xf-goe599-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8520 0.07313 0.07055 -0.0339 1.0000 0.0056
-13.000 -0.9066 0.05575 0.05283 -0.0469 1.0000 0.0054
-12.750 -0.9277 0.04682 0.04366 -0.0552 1.0000 0.0054
-12.500 -0.9426 0.04111 0.03773 -0.0598 1.0000 0.0054
-12.250 -0.9556 0.03753 0.03396 -0.0602 1.0000 0.0054
-12.000 -0.9663 0.03518 0.03144 -0.0578 1.0000 0.0055
-11.750 -0.9677 0.03313 0.02923 -0.0557 1.0000 0.0056
-11.500 -0.9646 0.03143 0.02737 -0.0535 1.0000 0.0057
-11.250 -0.9586 0.02989 0.02568 -0.0514 1.0000 0.0058
-11.000 -0.9504 0.02846 0.02410 -0.0494 1.0000 0.0059
-10.750 -0.9405 0.02710 0.02257 -0.0474 1.0000 0.0060
-10.500 -0.9291 0.02581 0.02112 -0.0455 1.0000 0.0062
-10.250 -0.9164 0.02455 0.01969 -0.0436 1.0000 0.0064
-10.000 -0.9025 0.02335 0.01831 -0.0419 1.0000 0.0066
-9.750 -0.8873 0.02223 0.01702 -0.0402 1.0000 0.0069
-9.500 -0.8706 0.02127 0.01590 -0.0387 1.0000 0.0071
-9.250 -0.8525 0.02044 0.01492 -0.0374 1.0000 0.0074
-9.000 -0.8334 0.01926 0.01360 -0.0364 0.9997 0.0078
-8.750 -0.8057 0.01833 0.01257 -0.0372 0.9983 0.0083
-8.500 -0.7767 0.01757 0.01172 -0.0380 0.9969 0.0087
-8.250 -0.7470 0.01683 0.01085 -0.0390 0.9955 0.0092
-8.000 -0.7172 0.01610 0.01002 -0.0399 0.9942 0.0098
-7.750 -0.6884 0.01545 0.00925 -0.0405 0.9923 0.0104
-7.500 -0.6591 0.01470 0.00841 -0.0413 0.9903 0.0113
-7.250 -0.6283 0.01416 0.00784 -0.0423 0.9885 0.0126
-7.000 -0.5965 0.01372 0.00734 -0.0435 0.9870 0.0139
-6.750 -0.5640 0.01327 0.00679 -0.0448 0.9858 0.0152
-6.500 -0.5353 0.01273 0.00623 -0.0453 0.9829 0.0174
-6.250 -0.5043 0.01239 0.00588 -0.0462 0.9804 0.0203
-6.000 -0.4716 0.01211 0.00555 -0.0475 0.9784 0.0226
-5.750 -0.4387 0.01165 0.00509 -0.0488 0.9768 0.0265
-5.500 -0.4045 0.01136 0.00475 -0.0504 0.9754 0.0301
-5.250 -0.3761 0.01112 0.00446 -0.0506 0.9711 0.0323
-5.000 -0.3452 0.01073 0.00406 -0.0515 0.9677 0.0369
-4.750 -0.3128 0.01044 0.00375 -0.0526 0.9650 0.0411
-4.500 -0.2830 0.01014 0.00344 -0.0531 0.9609 0.0481
-4.250 -0.2549 0.00976 0.00317 -0.0533 0.9554 0.0698
-4.000 -0.2239 0.00946 0.00296 -0.0542 0.9513 0.0981
-3.750 -0.1959 0.00929 0.00277 -0.0542 0.9446 0.1083
-3.500 -0.1663 0.00907 0.00256 -0.0546 0.9382 0.1177
-3.250 -0.1379 0.00883 0.00237 -0.0548 0.9305 0.1318
-3.000 -0.1094 0.00847 0.00216 -0.0551 0.9222 0.1770
-2.750 -0.0820 0.00813 0.00201 -0.0552 0.9116 0.2333
-2.500 -0.0536 0.00787 0.00187 -0.0553 0.8997 0.2723
-2.250 -0.0250 0.00766 0.00169 -0.0554 0.8816 0.3016
-2.000 0.0025 0.00750 0.00153 -0.0552 0.8563 0.3354
-1.750 0.0289 0.00731 0.00142 -0.0549 0.8344 0.3882
-1.500 0.0557 0.00713 0.00136 -0.0548 0.8215 0.4439
-1.250 0.0830 0.00701 0.00133 -0.0547 0.8113 0.4829
-1.000 0.1105 0.00694 0.00132 -0.0546 0.8017 0.5166
-0.750 0.1380 0.00689 0.00131 -0.0546 0.7926 0.5464
-0.500 0.1653 0.00685 0.00131 -0.0544 0.7787 0.5740
-0.250 0.1918 0.00683 0.00130 -0.0541 0.7559 0.6020
0.000 0.2177 0.00686 0.00128 -0.0536 0.7240 0.6261
0.250 0.2441 0.00687 0.00128 -0.0532 0.6967 0.6523
0.500 0.2701 0.00688 0.00129 -0.0528 0.6685 0.6802
0.750 0.2955 0.00695 0.00133 -0.0522 0.6325 0.7103
1.000 0.3200 0.00708 0.00138 -0.0515 0.5879 0.7432
1.250 0.3429 0.00728 0.00149 -0.0505 0.5268 0.7860
1.500 0.3640 0.00754 0.00164 -0.0490 0.4570 0.8407
1.750 0.3846 0.00778 0.00182 -0.0472 0.3987 0.9070
2.000 0.4159 0.00811 0.00200 -0.0479 0.3456 0.9633
2.250 0.4526 0.00864 0.00220 -0.0503 0.2686 0.9888
2.500 0.4837 0.00959 0.00256 -0.0517 0.1336 1.0000
2.750 0.5052 0.01012 0.00281 -0.0507 0.0682 1.0000
3.000 0.5299 0.01033 0.00298 -0.0501 0.0625 1.0000
3.250 0.5549 0.01054 0.00317 -0.0496 0.0589 1.0000
3.500 0.5801 0.01076 0.00339 -0.0491 0.0560 1.0000
3.750 0.6052 0.01101 0.00365 -0.0486 0.0536 1.0000
4.000 0.6307 0.01123 0.00388 -0.0482 0.0524 1.0000
4.250 0.6563 0.01145 0.00412 -0.0479 0.0514 1.0000
4.500 0.6817 0.01169 0.00440 -0.0475 0.0504 1.0000
4.750 0.7069 0.01197 0.00470 -0.0470 0.0494 1.0000
5.000 0.7320 0.01226 0.00503 -0.0466 0.0485 1.0000
5.250 0.7569 0.01258 0.00539 -0.0461 0.0475 1.0000
5.500 0.7817 0.01291 0.00576 -0.0456 0.0465 1.0000
5.750 0.8064 0.01324 0.00610 -0.0452 0.0446 1.0000
6.000 0.8296 0.01373 0.00660 -0.0445 0.0417 1.0000
6.250 0.8544 0.01404 0.00694 -0.0440 0.0403 1.0000
6.500 0.8801 0.01423 0.00719 -0.0438 0.0390 1.0000
6.750 0.9058 0.01442 0.00741 -0.0435 0.0368 1.0000
7.000 0.9314 0.01462 0.00763 -0.0432 0.0344 1.0000
7.250 0.9560 0.01493 0.00791 -0.0428 0.0318 1.0000
7.500 0.9815 0.01511 0.00816 -0.0425 0.0284 1.0000
7.750 1.0063 0.01537 0.00839 -0.0422 0.0216 1.0000
8.000 1.0290 0.01586 0.00882 -0.0415 0.0158 1.0000
8.250 1.0504 0.01649 0.00945 -0.0405 0.0130 1.0000
8.500 1.0720 0.01709 0.01012 -0.0395 0.0116 1.0000
8.750 1.0933 0.01769 0.01081 -0.0386 0.0105 1.0000
9.000 1.1138 0.01837 0.01155 -0.0375 0.0096 1.0000
9.250 1.1330 0.01918 0.01242 -0.0363 0.0087 1.0000
9.500 1.1520 0.01998 0.01333 -0.0350 0.0081 1.0000
9.750 1.1714 0.02070 0.01418 -0.0339 0.0078 1.0000
10.000 1.1898 0.02149 0.01508 -0.0326 0.0074 1.0000
10.250 1.2074 0.02233 0.01602 -0.0312 0.0070 1.0000
10.500 1.2241 0.02322 0.01701 -0.0297 0.0067 1.0000
10.750 1.2398 0.02414 0.01803 -0.0281 0.0065 1.0000
11.000 1.2536 0.02513 0.01912 -0.0263 0.0062 1.0000
11.250 1.2628 0.02631 0.02040 -0.0237 0.0059 1.0000
11.500 1.2688 0.02774 0.02196 -0.0209 0.0057 1.0000
11.750 1.2793 0.02882 0.02318 -0.0188 0.0055 1.0000
12.000 1.2885 0.03002 0.02455 -0.0167 0.0053 1.0000
12.250 1.2954 0.03142 0.02609 -0.0145 0.0052 1.0000
12.500 1.3006 0.03298 0.02781 -0.0123 0.0050 1.0000
12.750 1.3042 0.03473 0.02971 -0.0103 0.0049 1.0000
13.000 1.3062 0.03667 0.03181 -0.0084 0.0048 1.0000
13.250 1.3065 0.03886 0.03417 -0.0068 0.0047 1.0000
13.500 1.3057 0.04129 0.03676 -0.0055 0.0046 1.0000
13.750 1.3030 0.04403 0.03967 -0.0046 0.0045 1.0000
14.000 1.2986 0.04716 0.04296 -0.0042 0.0045 1.0000
14.250 1.2920 0.05072 0.04669 -0.0042 0.0044 1.0000
14.500 1.2836 0.05479 0.05093 -0.0049 0.0044 1.0000
14.750 1.2725 0.05954 0.05585 -0.0062 0.0043 1.0000
15.000 1.2586 0.06512 0.06161 -0.0085 0.0043 1.0000
15.250 1.2411 0.07180 0.06848 -0.0117 0.0043 1.0000
15.500 1.2200 0.07968 0.07655 -0.0160 0.0043 1.0000
15.750 1.1936 0.08925 0.08632 -0.0214 0.0044 1.0000
16.000 1.1589 0.10114 0.09843 -0.0282 0.0044 1.0000
16.250 1.1106 0.11714 0.11466 -0.0369 0.0046 1.0000
16.500 1.0250 0.14400 0.14176 -0.0502 0.0050 1.0000
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