GOE 600 AIRFOIL (goe600-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 600 AIRFOIL (goe600-il) Reynolds number: 100,000 Max Cl/Cd: 51.15 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe600-il-100000.txt Download as CSV file: xf-goe600-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 600 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5545 0.09233 0.08735 -0.0360 1.0000 0.0913
-10.250 -0.5424 0.09134 0.08637 -0.0344 1.0000 0.0982
-10.000 -0.7335 0.06011 0.05441 -0.0554 1.0000 0.0695
-9.750 -0.7377 0.05566 0.04975 -0.0542 1.0000 0.0689
-9.500 -0.7430 0.05142 0.04526 -0.0524 1.0000 0.0686
-9.250 -0.7478 0.04754 0.04105 -0.0499 1.0000 0.0685
-9.000 -0.7510 0.04409 0.03719 -0.0469 1.0000 0.0688
-8.750 -0.7516 0.04086 0.03357 -0.0440 1.0000 0.0699
-8.500 -0.7403 0.03902 0.03181 -0.0422 1.0000 0.0725
-8.250 -0.7314 0.03723 0.02986 -0.0398 1.0000 0.0748
-8.000 -0.7237 0.03494 0.02723 -0.0371 1.0000 0.0768
-7.750 -0.7143 0.03283 0.02466 -0.0345 1.0000 0.0794
-7.500 -0.7021 0.03104 0.02270 -0.0325 1.0000 0.0831
-7.250 -0.6878 0.03007 0.02168 -0.0307 1.0000 0.0876
-7.000 -0.6731 0.02876 0.02001 -0.0287 1.0000 0.0925
-6.750 -0.6573 0.02764 0.01896 -0.0273 1.0000 0.0983
-6.500 -0.6408 0.02682 0.01789 -0.0257 1.0000 0.1054
-6.250 -0.6235 0.02583 0.01695 -0.0245 1.0000 0.1130
-6.000 -0.6051 0.02502 0.01593 -0.0233 1.0000 0.1224
-5.750 -0.5860 0.02428 0.01521 -0.0224 1.0000 0.1335
-5.500 -0.5661 0.02335 0.01434 -0.0216 1.0000 0.1465
-5.250 -0.5458 0.02243 0.01342 -0.0209 1.0000 0.1652
-5.000 -0.5155 0.02120 0.01242 -0.0222 0.9973 0.1975
-4.750 -0.4781 0.02035 0.01187 -0.0250 0.9928 0.2373
-4.500 -0.4422 0.01982 0.01154 -0.0274 0.9874 0.2780
-4.250 -0.4037 0.01931 0.01134 -0.0302 0.9830 0.3377
-4.000 -0.3722 0.01883 0.01132 -0.0315 0.9768 0.4279
-3.750 -0.3363 0.01880 0.01159 -0.0333 0.9714 0.5135
-3.500 -0.3054 0.01895 0.01180 -0.0340 0.9652 0.5689
-3.250 -0.2732 0.01907 0.01197 -0.0349 0.9594 0.6089
-3.000 -0.2348 0.01918 0.01209 -0.0369 0.9550 0.6454
-2.750 -0.2109 0.01926 0.01220 -0.0362 0.9474 0.6738
-2.500 -0.1772 0.01934 0.01230 -0.0373 0.9424 0.7037
-2.250 -0.1472 0.01946 0.01244 -0.0377 0.9369 0.7325
-2.000 -0.1214 0.01958 0.01260 -0.0372 0.9303 0.7628
-1.750 -0.0878 0.01970 0.01276 -0.0379 0.9257 0.7949
-1.500 -0.0670 0.01991 0.01302 -0.0362 0.9187 0.8253
-1.250 -0.0381 0.02006 0.01321 -0.0359 0.9127 0.8590
-1.000 0.0031 0.02021 0.01335 -0.0374 0.9075 0.8940
-0.750 0.0448 0.02041 0.01354 -0.0395 0.8991 0.9292
-0.500 0.1200 0.02043 0.01347 -0.0479 0.8954 0.9555
-0.250 0.1991 0.02029 0.01323 -0.0577 0.8930 0.9702
0.000 0.2643 0.02030 0.01320 -0.0658 0.8862 0.9863
0.250 0.3376 0.01995 0.01281 -0.0751 0.8818 0.9996
0.500 0.3470 0.01997 0.01278 -0.0731 0.8707 1.0000
0.750 0.3723 0.01977 0.01253 -0.0731 0.8628 1.0000
1.000 0.3801 0.02001 0.01273 -0.0703 0.8509 1.0000
1.250 0.4021 0.02005 0.01273 -0.0694 0.8419 1.0000
1.500 0.4279 0.01999 0.01264 -0.0688 0.8329 1.0000
1.750 0.4462 0.02017 0.01280 -0.0672 0.8218 1.0000
2.000 0.4807 0.01983 0.01244 -0.0675 0.8151 1.0000
2.250 0.4994 0.01998 0.01259 -0.0658 0.8027 1.0000
2.500 0.5225 0.02000 0.01261 -0.0645 0.7913 1.0000
2.750 0.5534 0.01964 0.01226 -0.0640 0.7825 1.0000
3.000 0.5785 0.01948 0.01211 -0.0628 0.7704 1.0000
3.250 0.6027 0.01936 0.01201 -0.0614 0.7571 1.0000
3.500 0.6282 0.01916 0.01184 -0.0601 0.7436 1.0000
3.750 0.6543 0.01893 0.01161 -0.0589 0.7297 1.0000
4.000 0.6806 0.01870 0.01140 -0.0576 0.7151 1.0000
4.250 0.7066 0.01851 0.01123 -0.0564 0.6994 1.0000
4.500 0.7323 0.01836 0.01110 -0.0552 0.6826 1.0000
4.750 0.7581 0.01817 0.01091 -0.0539 0.6642 1.0000
5.000 0.7844 0.01793 0.01066 -0.0527 0.6448 1.0000
5.250 0.8078 0.01781 0.01057 -0.0512 0.6209 1.0000
5.500 0.8332 0.01757 0.01028 -0.0499 0.5970 1.0000
5.750 0.8556 0.01751 0.01023 -0.0483 0.5680 1.0000
6.000 0.8782 0.01754 0.01022 -0.0469 0.5379 1.0000
6.250 0.9007 0.01772 0.01033 -0.0455 0.5077 1.0000
6.500 0.9227 0.01804 0.01054 -0.0442 0.4775 1.0000
6.750 0.9441 0.01855 0.01091 -0.0429 0.4474 1.0000
7.000 0.9645 0.01920 0.01142 -0.0415 0.4172 1.0000
7.250 0.9836 0.01992 0.01201 -0.0400 0.3861 1.0000
7.500 1.0011 0.02064 0.01262 -0.0383 0.3546 1.0000
7.750 1.0173 0.02135 0.01326 -0.0365 0.3238 1.0000
8.000 1.0322 0.02209 0.01392 -0.0346 0.2934 1.0000
8.250 1.0459 0.02290 0.01465 -0.0326 0.2636 1.0000
8.500 1.0589 0.02382 0.01548 -0.0305 0.2354 1.0000
8.750 1.0707 0.02485 0.01642 -0.0283 0.2091 1.0000
9.000 1.0806 0.02603 0.01746 -0.0260 0.1846 1.0000
9.250 1.0880 0.02731 0.01865 -0.0234 0.1595 1.0000
9.500 1.0921 0.02881 0.02006 -0.0203 0.1345 1.0000
9.750 1.0948 0.03056 0.02159 -0.0172 0.1153 1.0000
10.000 1.1027 0.03231 0.02327 -0.0148 0.1008 1.0000
10.250 1.1168 0.03424 0.02499 -0.0134 0.0903 1.0000
10.500 1.1295 0.03581 0.02678 -0.0116 0.0826 1.0000
10.750 1.1531 0.03803 0.02891 -0.0113 0.0761 1.0000
11.000 1.1679 0.03982 0.03092 -0.0098 0.0713 1.0000
11.250 1.1975 0.04249 0.03341 -0.0107 0.0659 1.0000
11.500 1.2058 0.04446 0.03576 -0.0084 0.0637 1.0000
11.750 1.2165 0.04687 0.03848 -0.0067 0.0614 1.0000
12.000 1.2253 0.04914 0.04095 -0.0051 0.0592 1.0000
12.250 1.2357 0.05137 0.04324 -0.0038 0.0570 1.0000
12.500 1.2452 0.05500 0.04700 -0.0029 0.0551 1.0000
12.750 1.2348 0.05780 0.05017 0.0000 0.0546 1.0000
13.000 1.2233 0.06113 0.05384 0.0023 0.0543 1.0000
13.250 1.2087 0.06484 0.05787 0.0041 0.0541 1.0000
13.500 1.1914 0.06895 0.06228 0.0054 0.0540 1.0000
13.750 1.1718 0.07352 0.06713 0.0059 0.0540 1.0000
14.000 1.1499 0.07861 0.07248 0.0057 0.0541 1.0000
14.250 1.1263 0.08425 0.07836 0.0046 0.0543 1.0000
14.500 1.1012 0.09054 0.08485 0.0027 0.0546 1.0000
14.750 1.0756 0.09744 0.09194 -0.0001 0.0549 1.0000
15.000 1.0507 0.10498 0.09964 -0.0035 0.0553 1.0000
15.250 0.8559 0.16294 0.15787 -0.0417 0.0792 1.0000
15.500 0.8661 0.16580 0.16076 -0.0413 0.0782 1.0000
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