GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 623 AIRFOIL (goe623-il) Reynolds number: 200,000 Max Cl/Cd: 72.25 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe623-il-200000-n5.txt Download as CSV file: xf-goe623-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 623 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4145 0.08779 0.08421 -0.0427 1.0000 0.0245
-9.750 -0.4312 0.08047 0.07696 -0.0465 1.0000 0.0248
-9.250 -0.5655 0.04144 0.03728 -0.0753 0.9839 0.0243
-9.000 -0.5581 0.03441 0.02932 -0.0795 0.9740 0.0254
-8.750 -0.5390 0.03136 0.02584 -0.0807 0.9653 0.0265
-8.500 -0.5118 0.02993 0.02431 -0.0821 0.9595 0.0274
-8.250 -0.4866 0.02833 0.02248 -0.0829 0.9520 0.0284
-8.000 -0.4594 0.02651 0.02034 -0.0839 0.9463 0.0295
-7.750 -0.4342 0.02502 0.01851 -0.0842 0.9383 0.0309
-7.500 -0.4049 0.02375 0.01685 -0.0850 0.9328 0.0321
-7.250 -0.3806 0.02213 0.01505 -0.0850 0.9246 0.0332
-7.000 -0.3524 0.02103 0.01385 -0.0855 0.9183 0.0342
-6.750 -0.3258 0.02024 0.01295 -0.0855 0.9106 0.0356
-6.500 -0.2982 0.01943 0.01199 -0.0856 0.9036 0.0370
-6.250 -0.2714 0.01862 0.01103 -0.0854 0.8959 0.0380
-6.000 -0.2446 0.01789 0.01014 -0.0852 0.8882 0.0390
-5.750 -0.2178 0.01732 0.00942 -0.0849 0.8805 0.0400
-5.500 -0.1923 0.01650 0.00859 -0.0846 0.8725 0.0416
-5.250 -0.1661 0.01595 0.00799 -0.0843 0.8644 0.0429
-5.000 -0.1396 0.01547 0.00743 -0.0839 0.8560 0.0441
-4.750 -0.1132 0.01505 0.00693 -0.0836 0.8474 0.0456
-4.500 -0.0864 0.01466 0.00645 -0.0832 0.8392 0.0472
-4.250 -0.0598 0.01431 0.00603 -0.0829 0.8302 0.0494
-4.000 -0.0329 0.01395 0.00562 -0.0826 0.8218 0.0529
-3.750 -0.0062 0.01366 0.00528 -0.0823 0.8116 0.0571
-3.500 0.0207 0.01333 0.00494 -0.0820 0.8024 0.0647
-3.250 0.0475 0.01300 0.00462 -0.0817 0.7926 0.0806
-3.000 0.0742 0.01270 0.00445 -0.0815 0.7826 0.1105
-2.750 0.1017 0.01257 0.00429 -0.0813 0.7726 0.1376
-2.500 0.1288 0.01242 0.00414 -0.0811 0.7612 0.1558
-2.250 0.1561 0.01228 0.00398 -0.0809 0.7500 0.1711
-2.000 0.1833 0.01213 0.00382 -0.0807 0.7393 0.1872
-1.750 0.2105 0.01199 0.00367 -0.0805 0.7281 0.2025
-1.500 0.2375 0.01183 0.00357 -0.0803 0.7163 0.2279
-1.000 0.2903 0.01131 0.00340 -0.0799 0.6949 0.3553
-0.750 0.3148 0.01084 0.00337 -0.0793 0.6842 0.4856
-0.500 0.3371 0.01033 0.00340 -0.0780 0.6743 0.6483
0.000 0.3896 0.00993 0.00349 -0.0759 0.6548 0.8915
0.250 0.4295 0.00998 0.00345 -0.0782 0.6428 0.9511
0.500 0.4682 0.01007 0.00340 -0.0804 0.6307 0.9843
0.750 0.5046 0.01018 0.00337 -0.0822 0.6193 1.0000
1.000 0.5295 0.01030 0.00339 -0.0816 0.6081 1.0000
1.250 0.5545 0.01043 0.00341 -0.0810 0.5967 1.0000
1.500 0.5796 0.01058 0.00344 -0.0804 0.5856 1.0000
1.750 0.6050 0.01071 0.00349 -0.0800 0.5749 1.0000
2.000 0.6307 0.01084 0.00356 -0.0795 0.5654 1.0000
2.250 0.6563 0.01099 0.00363 -0.0791 0.5562 1.0000
2.500 0.6822 0.01112 0.00374 -0.0787 0.5469 1.0000
2.750 0.7079 0.01128 0.00383 -0.0783 0.5380 1.0000
3.000 0.7339 0.01142 0.00395 -0.0779 0.5286 1.0000
3.250 0.7597 0.01158 0.00407 -0.0775 0.5193 1.0000
3.500 0.7853 0.01175 0.00420 -0.0771 0.5085 1.0000
3.750 0.8109 0.01191 0.00434 -0.0767 0.4965 1.0000
4.000 0.8363 0.01208 0.00450 -0.0763 0.4840 1.0000
4.250 0.8616 0.01227 0.00466 -0.0758 0.4708 1.0000
4.500 0.8865 0.01247 0.00483 -0.0753 0.4561 1.0000
4.750 0.9112 0.01269 0.00502 -0.0748 0.4390 1.0000
5.000 0.9351 0.01295 0.00522 -0.0741 0.4186 1.0000
5.250 0.9581 0.01326 0.00545 -0.0733 0.3949 1.0000
5.750 1.0018 0.01408 0.00605 -0.0714 0.3461 1.0000
6.000 1.0232 0.01454 0.00642 -0.0705 0.3263 1.0000
6.250 1.0447 0.01501 0.00682 -0.0696 0.3095 1.0000
6.500 1.0662 0.01546 0.00723 -0.0687 0.2947 1.0000
6.750 1.0879 0.01591 0.00766 -0.0678 0.2818 1.0000
7.000 1.1094 0.01637 0.00811 -0.0669 0.2707 1.0000
7.250 1.1301 0.01687 0.00859 -0.0659 0.2609 1.0000
7.500 1.1513 0.01733 0.00907 -0.0650 0.2517 1.0000
7.750 1.1717 0.01782 0.00957 -0.0640 0.2439 1.0000
8.000 1.1922 0.01831 0.01008 -0.0629 0.2366 1.0000
8.250 1.2117 0.01884 0.01064 -0.0618 0.2297 1.0000
8.500 1.2314 0.01933 0.01118 -0.0607 0.2222 1.0000
8.750 1.2494 0.01991 0.01176 -0.0594 0.2155 1.0000
9.000 1.2682 0.02041 0.01232 -0.0582 0.2079 1.0000
9.250 1.2832 0.02101 0.01294 -0.0564 0.2006 1.0000
9.500 1.2994 0.02155 0.01354 -0.0549 0.1920 1.0000
9.750 1.3141 0.02219 0.01421 -0.0532 0.1837 1.0000
10.000 1.3273 0.02291 0.01494 -0.0514 0.1739 1.0000
10.250 1.3428 0.02356 0.01567 -0.0500 0.1644 1.0000
10.500 1.3560 0.02436 0.01652 -0.0484 0.1558 1.0000
10.750 1.3685 0.02523 0.01742 -0.0469 0.1453 1.0000
11.000 1.3809 0.02615 0.01839 -0.0454 0.1320 1.0000
11.250 1.3891 0.02741 0.01960 -0.0437 0.1076 1.0000
11.500 1.3813 0.02997 0.02180 -0.0409 0.0664 1.0000
11.750 1.3789 0.03228 0.02403 -0.0388 0.0523 1.0000
12.000 1.3803 0.03436 0.02616 -0.0372 0.0433 1.0000
12.250 1.3822 0.03647 0.02835 -0.0358 0.0366 1.0000
12.500 1.3834 0.03874 0.03069 -0.0346 0.0318 1.0000
12.750 1.3837 0.04117 0.03319 -0.0335 0.0282 1.0000
13.000 1.3841 0.04367 0.03580 -0.0327 0.0257 1.0000
13.250 1.3834 0.04639 0.03862 -0.0321 0.0237 1.0000
13.500 1.3799 0.04951 0.04184 -0.0317 0.0224 1.0000
13.750 1.3770 0.05268 0.04514 -0.0315 0.0213 1.0000
14.000 1.3733 0.05607 0.04868 -0.0315 0.0205 1.0000
14.250 1.3683 0.05973 0.05248 -0.0317 0.0198 1.0000
14.500 1.3619 0.06370 0.05659 -0.0322 0.0191 1.0000
14.750 1.3541 0.06801 0.06103 -0.0329 0.0186 1.0000
15.000 1.3443 0.07270 0.06583 -0.0339 0.0182 1.0000
15.250 1.3325 0.07782 0.07110 -0.0351 0.0178 1.0000
15.500 1.3215 0.08297 0.07637 -0.0365 0.0174 1.0000
15.750 1.3124 0.08792 0.08147 -0.0378 0.0171 1.0000
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