GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 702 AIRFOIL (goe702-il) Reynolds number: 500,000 Max Cl/Cd: 88.18 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe702-il-500000.txt Download as CSV file: xf-goe702-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 702 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7882 0.05056 0.04708 -0.0864 0.9254 0.0445
-14.250 -0.8089 0.04166 0.03773 -0.0981 0.8831 0.0447
-14.000 -0.8371 0.03637 0.03213 -0.1021 0.8566 0.0448
-13.750 -0.8514 0.03406 0.02962 -0.1011 0.8377 0.0450
-13.500 -0.8613 0.03232 0.02770 -0.0985 0.8222 0.0452
-13.000 -0.8639 0.02987 0.02490 -0.0930 0.7972 0.0460
-12.750 -0.8568 0.02875 0.02356 -0.0911 0.7878 0.0465
-12.500 -0.8462 0.02766 0.02230 -0.0895 0.7787 0.0468
-12.250 -0.8340 0.02658 0.02101 -0.0878 0.7709 0.0472
-12.000 -0.8199 0.02522 0.01959 -0.0865 0.7640 0.0478
-11.750 -0.8016 0.02439 0.01873 -0.0855 0.7572 0.0483
-11.500 -0.7823 0.02372 0.01797 -0.0844 0.7507 0.0489
-11.250 -0.7621 0.02305 0.01724 -0.0834 0.7442 0.0495
-11.000 -0.7416 0.02237 0.01646 -0.0824 0.7372 0.0502
-10.750 -0.7207 0.02176 0.01570 -0.0814 0.7309 0.0510
-10.500 -0.6988 0.02118 0.01498 -0.0805 0.7254 0.0517
-10.250 -0.6758 0.02067 0.01434 -0.0797 0.7199 0.0524
-10.000 -0.6556 0.01964 0.01327 -0.0787 0.7145 0.0533
-9.750 -0.6326 0.01912 0.01269 -0.0779 0.7090 0.0542
-9.500 -0.6085 0.01863 0.01218 -0.0772 0.7041 0.0550
-9.250 -0.5841 0.01815 0.01164 -0.0765 0.6987 0.0561
-9.000 -0.5594 0.01770 0.01108 -0.0759 0.6938 0.0571
-8.750 -0.5343 0.01735 0.01058 -0.0752 0.6894 0.0580
-8.500 -0.5108 0.01666 0.00989 -0.0745 0.6856 0.0593
-8.250 -0.4854 0.01625 0.00949 -0.0739 0.6814 0.0606
-8.000 -0.4594 0.01591 0.00911 -0.0734 0.6770 0.0621
-7.750 -0.4332 0.01559 0.00870 -0.0729 0.6726 0.0636
-7.500 -0.4077 0.01520 0.00821 -0.0723 0.6682 0.0651
-7.250 -0.3819 0.01478 0.00783 -0.0718 0.6646 0.0668
-7.000 -0.3551 0.01449 0.00752 -0.0714 0.6603 0.0686
-6.750 -0.3280 0.01423 0.00720 -0.0709 0.6558 0.0706
-6.500 -0.3018 0.01387 0.00681 -0.0704 0.6513 0.0729
-6.250 -0.2748 0.01369 0.00659 -0.0700 0.6467 0.0752
-6.000 -0.2470 0.01348 0.00636 -0.0697 0.6426 0.0779
-5.750 -0.2201 0.01316 0.00605 -0.0693 0.6379 0.0807
-5.500 -0.1924 0.01298 0.00586 -0.0690 0.6331 0.0837
-5.250 -0.1645 0.01290 0.00567 -0.0686 0.6280 0.0869
-5.000 -0.1373 0.01261 0.00544 -0.0683 0.6230 0.0907
-4.750 -0.1090 0.01248 0.00530 -0.0680 0.6175 0.0947
-4.500 -0.0816 0.01225 0.00505 -0.0676 0.6122 0.0989
-4.250 -0.0537 0.01216 0.00492 -0.0674 0.6068 0.1032
-4.000 -0.0256 0.01198 0.00473 -0.0671 0.6005 0.1077
-3.750 0.0020 0.01179 0.00456 -0.0668 0.5937 0.1123
-3.500 0.0301 0.01173 0.00442 -0.0665 0.5870 0.1166
-3.250 0.0577 0.01147 0.00421 -0.0662 0.5792 0.1214
-3.000 0.0854 0.01137 0.00406 -0.0659 0.5714 0.1260
-2.750 0.1139 0.01129 0.00395 -0.0657 0.5627 0.1297
-2.500 0.1408 0.01108 0.00373 -0.0653 0.5528 0.1352
-2.250 0.1687 0.01097 0.00362 -0.0650 0.5414 0.1400
-2.000 0.1963 0.01092 0.00349 -0.0647 0.5291 0.1443
-1.750 0.2231 0.01079 0.00335 -0.0643 0.5152 0.1506
-1.500 0.2505 0.01076 0.00327 -0.0640 0.5010 0.1566
-1.250 0.2773 0.01069 0.00319 -0.0636 0.4877 0.1646
-0.500 0.3571 0.01060 0.00314 -0.0624 0.4559 0.2180
-0.250 0.3837 0.01061 0.00320 -0.0620 0.4475 0.2492
0.000 0.4104 0.01067 0.00328 -0.0616 0.4405 0.2734
0.250 0.4378 0.01071 0.00335 -0.0614 0.4345 0.2913
0.500 0.4647 0.01081 0.00342 -0.0610 0.4286 0.3061
0.750 0.4914 0.01093 0.00351 -0.0607 0.4232 0.3205
1.000 0.5188 0.01095 0.00358 -0.0604 0.4186 0.3338
1.250 0.5459 0.01103 0.00366 -0.0601 0.4136 0.3460
1.500 0.5722 0.01113 0.00375 -0.0597 0.4088 0.3590
1.750 0.5986 0.01125 0.00386 -0.0593 0.4045 0.3720
2.000 0.6259 0.01128 0.00395 -0.0591 0.4010 0.3869
2.750 0.7042 0.01148 0.00428 -0.0578 0.3898 0.4505
3.000 0.7292 0.01151 0.00443 -0.0573 0.3862 0.4913
3.250 0.8021 0.01056 0.00476 -0.0663 0.3817 0.9792
3.500 0.8694 0.01076 0.00489 -0.0744 0.3772 1.0000
3.750 0.8930 0.01095 0.00502 -0.0735 0.3741 1.0000
4.000 0.9160 0.01120 0.00520 -0.0725 0.3708 1.0000
4.250 0.9397 0.01140 0.00538 -0.0717 0.3680 1.0000
4.500 0.9637 0.01153 0.00552 -0.0709 0.3656 1.0000
4.750 0.9874 0.01168 0.00566 -0.0701 0.3627 1.0000
5.000 1.0109 0.01185 0.00581 -0.0692 0.3598 1.0000
5.250 1.0341 0.01204 0.00597 -0.0683 0.3569 1.0000
5.500 1.0568 0.01230 0.00617 -0.0674 0.3540 1.0000
5.750 1.0797 0.01260 0.00644 -0.0665 0.3511 1.0000
6.000 1.1030 0.01275 0.00662 -0.0656 0.3491 1.0000
6.250 1.1261 0.01292 0.00681 -0.0647 0.3466 1.0000
6.500 1.1490 0.01311 0.00700 -0.0638 0.3440 1.0000
6.750 1.1716 0.01330 0.00719 -0.0629 0.3413 1.0000
7.000 1.1939 0.01354 0.00741 -0.0620 0.3388 1.0000
7.250 1.2159 0.01385 0.00767 -0.0610 0.3361 1.0000
7.500 1.2384 0.01417 0.00799 -0.0601 0.3336 1.0000
7.750 1.2600 0.01436 0.00822 -0.0591 0.3316 1.0000
8.000 1.2815 0.01456 0.00847 -0.0581 0.3292 1.0000
8.250 1.3026 0.01479 0.00872 -0.0570 0.3267 1.0000
8.500 1.3235 0.01504 0.00897 -0.0559 0.3245 1.0000
8.750 1.3438 0.01530 0.00924 -0.0548 0.3221 1.0000
9.000 1.3641 0.01564 0.00955 -0.0537 0.3195 1.0000
9.250 1.3853 0.01604 0.00993 -0.0527 0.3168 1.0000
9.500 1.4035 0.01629 0.01025 -0.0513 0.3151 1.0000
9.750 1.4192 0.01656 0.01058 -0.0494 0.3128 1.0000
10.000 1.4322 0.01683 0.01089 -0.0471 0.3099 1.0000
10.250 1.4452 0.01714 0.01122 -0.0450 0.3069 1.0000
10.500 1.4593 0.01755 0.01161 -0.0433 0.3038 1.0000
10.750 1.4774 0.01805 0.01208 -0.0422 0.3005 1.0000
11.000 1.4894 0.01852 0.01265 -0.0404 0.2982 1.0000
11.250 1.5028 0.01903 0.01323 -0.0390 0.2952 1.0000
11.500 1.5175 0.01958 0.01382 -0.0378 0.2925 1.0000
11.750 1.5321 0.02017 0.01444 -0.0367 0.2899 1.0000
12.000 1.5466 0.02082 0.01507 -0.0356 0.2869 1.0000
12.250 1.5614 0.02150 0.01577 -0.0345 0.2838 1.0000
12.500 1.5739 0.02227 0.01664 -0.0335 0.2812 1.0000
12.750 1.5869 0.02307 0.01751 -0.0326 0.2781 1.0000
13.000 1.5988 0.02395 0.01843 -0.0317 0.2747 1.0000
13.250 1.6100 0.02492 0.01939 -0.0308 0.2713 1.0000
13.500 1.6220 0.02588 0.02038 -0.0299 0.2680 1.0000
13.750 1.6331 0.02695 0.02156 -0.0293 0.2650 1.0000
14.000 1.6436 0.02809 0.02277 -0.0286 0.2617 1.0000
14.250 1.6530 0.02931 0.02403 -0.0279 0.2582 1.0000
14.500 1.6611 0.03062 0.02533 -0.0271 0.2546 1.0000
14.750 1.6699 0.03197 0.02677 -0.0265 0.2515 1.0000
15.000 1.6781 0.03340 0.02829 -0.0260 0.2478 1.0000
15.250 1.6842 0.03500 0.02994 -0.0254 0.2439 1.0000
15.500 1.6873 0.03687 0.03180 -0.0248 0.2397 1.0000
15.750 1.6928 0.03868 0.03372 -0.0244 0.2352 1.0000
16.000 1.6952 0.04082 0.03592 -0.0241 0.2298 1.0000
16.250 1.6925 0.04341 0.03850 -0.0237 0.2245 1.0000
16.500 1.6962 0.04553 0.04073 -0.0235 0.2197 1.0000
16.750 1.6921 0.04846 0.04369 -0.0233 0.2131 1.0000
17.000 1.6884 0.05139 0.04667 -0.0232 0.2077 1.0000
17.250 1.6825 0.05463 0.04998 -0.0232 0.2009 1.0000
17.500 1.6705 0.05860 0.05397 -0.0233 0.1935 1.0000
17.750 1.6572 0.06283 0.05824 -0.0236 0.1857 1.0000
18.000 1.6419 0.06735 0.06280 -0.0240 0.1779 1.0000
18.250 1.6178 0.07307 0.06851 -0.0247 0.1691 1.0000
18.500 1.5952 0.07870 0.07418 -0.0255 0.1597 1.0000
18.750 1.5704 0.08473 0.08024 -0.0266 0.1507 1.0000
19.000 1.5410 0.09146 0.08698 -0.0279 0.1412 1.0000
19.250 1.5110 0.09840 0.09391 -0.0295 0.1315 1.0000
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Polar data table (+)
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