GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il) Reynolds number: 200,000 Max Cl/Cd: 80 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe602m-il-200000.txt Download as CSV file: xf-goe602m-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 MOD. 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2913 0.09346 0.09027 -0.0349 1.0000 0.0463
-9.000 -0.2927 0.09108 0.08792 -0.0337 1.0000 0.0479
-8.750 -0.3806 0.09437 0.09103 -0.0382 1.0000 0.0442
-8.500 -0.3747 0.09239 0.08906 -0.0356 1.0000 0.0455
-8.250 -0.3768 0.09039 0.08711 -0.0339 1.0000 0.0467
-8.000 -0.3824 0.08859 0.08536 -0.0321 1.0000 0.0484
-7.750 -0.3939 0.08673 0.08357 -0.0301 1.0000 0.0492
-7.500 -0.4098 0.08509 0.08200 -0.0275 1.0000 0.0495
-7.250 -0.4282 0.08346 0.08045 -0.0253 1.0000 0.0513
-7.000 -0.4397 0.08069 0.07775 -0.0256 1.0000 0.0523
-6.250 -0.4264 0.06472 0.06174 -0.0425 0.9951 0.0578
-6.000 -0.4000 0.06127 0.05822 -0.0465 0.9905 0.0613
-5.750 -0.3618 0.05007 0.04650 -0.0632 0.9843 0.0699
-5.500 -0.3363 0.04823 0.04472 -0.0641 0.9794 0.0735
-5.250 -0.3023 0.04216 0.03816 -0.0715 0.9738 0.0840
-5.000 -0.2629 0.03064 0.02527 -0.0771 0.9710 0.0575
-4.750 -0.2334 0.02642 0.02052 -0.0777 0.9657 0.0501
-4.500 -0.1984 0.02345 0.01698 -0.0793 0.9615 0.0499
-4.250 -0.1586 0.02190 0.01500 -0.0815 0.9583 0.0535
-4.000 -0.1252 0.02056 0.01331 -0.0824 0.9530 0.0547
-3.750 -0.0914 0.01880 0.01142 -0.0837 0.9481 0.0585
-3.500 -0.0509 0.01782 0.01037 -0.0861 0.9448 0.0622
-3.250 -0.0175 0.01704 0.00949 -0.0871 0.9389 0.0653
-3.000 0.0183 0.01620 0.00863 -0.0885 0.9335 0.0706
-2.750 0.0596 0.01550 0.00795 -0.0911 0.9303 0.0771
-2.500 0.0911 0.01494 0.00739 -0.0917 0.9234 0.0855
-2.250 0.1292 0.01412 0.00673 -0.0937 0.9187 0.1268
-2.000 0.1697 0.01296 0.00639 -0.0966 0.9161 0.3464
-1.750 0.2003 0.01262 0.00622 -0.0970 0.9086 0.4055
-1.500 0.2375 0.01219 0.00601 -0.0987 0.9038 0.4789
-1.250 0.2771 0.01171 0.00575 -0.1007 0.9006 0.5657
-1.000 0.3014 0.01130 0.00561 -0.0996 0.8906 0.6371
-0.750 0.3354 0.01042 0.00537 -0.0997 0.8866 0.8284
-0.500 0.3999 0.01006 0.00505 -0.1071 0.8813 1.0000
-0.250 0.4341 0.00988 0.00475 -0.1080 0.8732 1.0000
0.000 0.4617 0.00981 0.00458 -0.1076 0.8619 1.0000
0.250 0.4908 0.00973 0.00439 -0.1075 0.8508 1.0000
0.500 0.5205 0.00963 0.00421 -0.1075 0.8396 1.0000
0.750 0.5494 0.00956 0.00404 -0.1074 0.8275 1.0000
1.000 0.5771 0.00952 0.00392 -0.1069 0.8139 1.0000
1.250 0.6037 0.00951 0.00383 -0.1063 0.7987 1.0000
1.500 0.6299 0.00952 0.00378 -0.1057 0.7824 1.0000
1.750 0.6562 0.00956 0.00373 -0.1050 0.7650 1.0000
2.000 0.6826 0.00962 0.00370 -0.1044 0.7473 1.0000
2.250 0.7092 0.00972 0.00368 -0.1038 0.7292 1.0000
2.500 0.7336 0.00985 0.00375 -0.1029 0.7084 1.0000
2.750 0.7587 0.01001 0.00380 -0.1021 0.6882 1.0000
3.000 0.7831 0.01019 0.00390 -0.1012 0.6677 1.0000
3.250 0.8074 0.01038 0.00402 -0.1003 0.6476 1.0000
3.500 0.8318 0.01061 0.00418 -0.0994 0.6287 1.0000
3.750 0.8554 0.01083 0.00435 -0.0984 0.6082 1.0000
4.000 0.8790 0.01107 0.00453 -0.0974 0.5882 1.0000
4.250 0.9027 0.01133 0.00473 -0.0965 0.5698 1.0000
4.500 0.9262 0.01159 0.00499 -0.0956 0.5513 1.0000
4.750 0.9488 0.01186 0.00522 -0.0944 0.5301 1.0000
5.000 0.9691 0.01215 0.00541 -0.0929 0.5011 1.0000
5.250 0.9894 0.01247 0.00564 -0.0913 0.4721 1.0000
5.500 1.0100 0.01281 0.00593 -0.0899 0.4451 1.0000
5.750 1.0294 0.01320 0.00623 -0.0883 0.4137 1.0000
6.000 1.0483 0.01362 0.00655 -0.0866 0.3790 1.0000
6.250 1.0660 0.01413 0.00692 -0.0848 0.3386 1.0000
6.500 1.0809 0.01484 0.00737 -0.0826 0.2828 1.0000
6.750 1.0913 0.01599 0.00805 -0.0798 0.2024 1.0000
7.000 1.0964 0.01773 0.00908 -0.0765 0.1017 1.0000
7.250 1.1058 0.01917 0.01012 -0.0736 0.0444 1.0000
7.500 1.1195 0.02022 0.01111 -0.0712 0.0358 1.0000
7.750 1.1352 0.02105 0.01207 -0.0691 0.0334 1.0000
8.000 1.1468 0.02203 0.01319 -0.0664 0.0307 1.0000
8.250 1.1548 0.02316 0.01445 -0.0633 0.0288 1.0000
8.500 1.1592 0.02451 0.01591 -0.0597 0.0277 1.0000
8.750 1.1619 0.02606 0.01756 -0.0561 0.0270 1.0000
9.000 1.1683 0.02751 0.01910 -0.0531 0.0266 1.0000
9.250 1.1771 0.02894 0.02061 -0.0505 0.0262 1.0000
9.500 1.1877 0.03047 0.02223 -0.0483 0.0260 1.0000
9.750 1.2014 0.03215 0.02399 -0.0465 0.0258 1.0000
10.000 1.2175 0.03380 0.02575 -0.0450 0.0253 1.0000
10.250 1.2330 0.03540 0.02749 -0.0436 0.0242 1.0000
10.500 1.2522 0.03740 0.02964 -0.0426 0.0238 1.0000
10.750 1.2737 0.03980 0.03225 -0.0418 0.0239 1.0000
11.000 1.2935 0.04269 0.03540 -0.0409 0.0245 1.0000
11.250 1.3086 0.04627 0.03930 -0.0397 0.0253 1.0000
11.500 1.3425 0.05165 0.04491 -0.0412 0.0273 1.0000
11.750 1.3352 0.05206 0.04571 -0.0362 0.0291 1.0000
12.000 1.3137 0.05785 0.05219 -0.0317 0.0334 1.0000
14.000 1.0274 0.09693 0.09337 -0.0297 0.0344 1.0000
14.250 0.9928 0.10371 0.10036 -0.0345 0.0338 1.0000
14.500 0.9589 0.11187 0.10871 -0.0406 0.0333 1.0000
14.750 0.9256 0.12106 0.11807 -0.0476 0.0328 1.0000
15.000 0.8873 0.13270 0.12984 -0.0563 0.0324 1.0000
15.250 0.8441 0.14777 0.14495 -0.0659 0.0340 1.0000
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