GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 500,000 Max Cl/Cd: 108.14 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe758-il-500000.txt Download as CSV file: xf-goe758-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1342 0.08388 0.08171 -0.0679 0.9506 0.0330
-10.000 -0.1436 0.07409 0.07189 -0.0774 0.9422 0.0356
-9.750 -0.1458 0.06507 0.06285 -0.0843 0.9302 0.0361
-9.500 -0.1214 0.06241 0.06009 -0.0869 0.9119 0.0367
-9.250 -0.1096 0.05951 0.05710 -0.0887 0.8920 0.0371
-9.000 -0.1063 0.05642 0.05393 -0.0897 0.8737 0.0376
-8.750 -0.1054 0.05338 0.05084 -0.0904 0.8564 0.0385
-8.500 -0.1125 0.04918 0.04659 -0.0920 0.8401 0.0392
-8.250 -0.1305 0.04345 0.04082 -0.0952 0.8245 0.0401
-8.000 -0.1812 0.03449 0.03171 -0.1022 0.8088 0.0394
-7.750 -0.2222 0.02816 0.02463 -0.1031 0.7917 0.0425
-7.500 -0.2257 0.02218 0.01850 -0.1030 0.7765 0.0437
-7.250 -0.2087 0.02083 0.01710 -0.1024 0.7573 0.0444
-7.000 -0.1932 0.01941 0.01554 -0.1018 0.7383 0.0453
-6.750 -0.1779 0.01784 0.01377 -0.1011 0.7209 0.0469
-6.500 -0.1715 0.01477 0.01011 -0.0998 0.7067 0.0519
-6.250 -0.1506 0.01369 0.00899 -0.0995 0.6946 0.0529
-6.000 -0.1299 0.01279 0.00797 -0.0990 0.6843 0.0547
-5.750 -0.1132 0.01138 0.00611 -0.0980 0.6756 0.0614
-5.500 -0.0902 0.01055 0.00530 -0.0979 0.6681 0.0630
-5.250 -0.0680 0.01831 0.01176 -0.0999 0.6723 0.0416
-5.000 -0.0443 0.01671 0.00994 -0.0992 0.6651 0.0400
-4.750 -0.0192 0.01565 0.00869 -0.0985 0.6584 0.0389
-4.500 0.0062 0.01491 0.00777 -0.0979 0.6523 0.0385
-4.250 0.0322 0.01434 0.00714 -0.0975 0.6467 0.0388
-4.000 0.0581 0.01381 0.00654 -0.0971 0.6411 0.0392
-3.750 0.0839 0.01335 0.00598 -0.0966 0.6361 0.0392
-3.500 0.1099 0.01291 0.00550 -0.0961 0.6313 0.0393
-3.250 0.1358 0.01253 0.00508 -0.0957 0.6263 0.0397
-3.000 0.1617 0.01223 0.00471 -0.0952 0.6214 0.0400
-2.750 0.1877 0.01196 0.00439 -0.0948 0.6168 0.0403
-2.500 0.2139 0.01168 0.00410 -0.0944 0.6119 0.0408
-2.250 0.2402 0.01147 0.00384 -0.0940 0.6072 0.0415
-2.000 0.2668 0.01136 0.00365 -0.0937 0.6027 0.0423
-1.750 0.2932 0.01111 0.00340 -0.0934 0.5986 0.0433
-1.500 0.3198 0.01090 0.00317 -0.0931 0.5941 0.0446
-1.250 0.3466 0.01077 0.00300 -0.0928 0.5899 0.0464
-1.000 0.3739 0.01075 0.00290 -0.0926 0.5857 0.0486
-0.750 0.4009 0.01063 0.00281 -0.0923 0.5817 0.0526
-0.500 0.4267 0.01031 0.00273 -0.0920 0.5773 0.1174
-0.250 0.4499 0.00967 0.00268 -0.0914 0.5731 0.3129
0.000 0.4731 0.00924 0.00275 -0.0908 0.5691 0.4832
0.250 0.4971 0.00897 0.00282 -0.0900 0.5650 0.5909
0.500 0.5219 0.00882 0.00285 -0.0892 0.5604 0.6531
0.750 0.5458 0.00866 0.00287 -0.0883 0.5561 0.7178
1.000 0.5672 0.00835 0.00294 -0.0867 0.5519 0.8386
1.250 0.6618 0.00823 0.00300 -0.1009 0.5452 0.9977
1.500 0.6910 0.00830 0.00300 -0.1012 0.5403 1.0000
1.750 0.7156 0.00840 0.00303 -0.1005 0.5356 1.0000
2.000 0.7403 0.00845 0.00306 -0.0999 0.5303 1.0000
2.250 0.7651 0.00852 0.00309 -0.0992 0.5252 1.0000
2.500 0.7897 0.00863 0.00314 -0.0986 0.5202 1.0000
2.750 0.8146 0.00868 0.00319 -0.0979 0.5142 1.0000
3.000 0.8391 0.00877 0.00324 -0.0973 0.5084 1.0000
3.250 0.8638 0.00887 0.00331 -0.0966 0.5027 1.0000
3.500 0.8885 0.00895 0.00338 -0.0960 0.4961 1.0000
4.000 0.9374 0.00916 0.00356 -0.0947 0.4828 1.0000
4.250 0.9614 0.00930 0.00364 -0.0939 0.4760 1.0000
4.500 0.9860 0.00941 0.00377 -0.0933 0.4689 1.0000
4.750 1.0098 0.00956 0.00388 -0.0925 0.4613 1.0000
5.000 1.0340 0.00970 0.00402 -0.0919 0.4536 1.0000
5.250 1.0571 0.00988 0.00415 -0.0910 0.4448 1.0000
5.500 1.0808 0.01003 0.00430 -0.0903 0.4353 1.0000
5.750 1.1034 0.01023 0.00446 -0.0893 0.4259 1.0000
6.000 1.1266 0.01042 0.00464 -0.0885 0.4170 1.0000
6.250 1.1495 0.01063 0.00484 -0.0877 0.4091 1.0000
6.500 1.1722 0.01085 0.00505 -0.0868 0.4011 1.0000
6.750 1.1946 0.01108 0.00528 -0.0859 0.3935 1.0000
7.000 1.2162 0.01133 0.00551 -0.0849 0.3846 1.0000
7.250 1.2380 0.01156 0.00575 -0.0839 0.3756 1.0000
7.500 1.2578 0.01188 0.00602 -0.0826 0.3663 1.0000
7.750 1.2793 0.01211 0.00628 -0.0816 0.3575 1.0000
8.000 1.2989 0.01242 0.00658 -0.0802 0.3494 1.0000
8.250 1.3182 0.01271 0.00687 -0.0789 0.3397 1.0000
8.500 1.3369 0.01302 0.00718 -0.0774 0.3299 1.0000
8.750 1.3525 0.01339 0.00752 -0.0754 0.3216 1.0000
9.000 1.3702 0.01366 0.00784 -0.0737 0.3137 1.0000
9.250 1.3835 0.01407 0.00823 -0.0713 0.3053 1.0000
9.500 1.3999 0.01440 0.00859 -0.0695 0.2959 1.0000
9.750 1.4141 0.01483 0.00902 -0.0674 0.2866 1.0000
10.000 1.4258 0.01536 0.00954 -0.0651 0.2747 1.0000
10.250 1.4379 0.01592 0.01008 -0.0629 0.2621 1.0000
10.500 1.4469 0.01664 0.01076 -0.0604 0.2449 1.0000
10.750 1.4510 0.01765 0.01167 -0.0574 0.2206 1.0000
11.000 1.4497 0.01904 0.01292 -0.0541 0.1922 1.0000
11.250 1.4387 0.02115 0.01479 -0.0501 0.1532 1.0000
11.500 1.4175 0.02419 0.01755 -0.0459 0.1075 1.0000
11.750 1.4044 0.02702 0.02025 -0.0430 0.0838 1.0000
12.000 1.3961 0.02971 0.02289 -0.0409 0.0664 1.0000
12.250 1.3845 0.03290 0.02596 -0.0391 0.0435 1.0000
12.500 1.3732 0.03631 0.02931 -0.0378 0.0313 1.0000
12.750 1.3683 0.03929 0.03232 -0.0369 0.0274 1.0000
13.000 1.3685 0.04183 0.03495 -0.0363 0.0256 1.0000
13.250 1.3669 0.04465 0.03784 -0.0358 0.0241 1.0000
13.500 1.3641 0.04764 0.04090 -0.0354 0.0232 1.0000
13.750 1.3583 0.05103 0.04438 -0.0350 0.0223 1.0000
14.000 1.3570 0.05401 0.04746 -0.0348 0.0216 1.0000
14.250 1.3549 0.05710 0.05064 -0.0347 0.0211 1.0000
14.500 1.3512 0.06046 0.05408 -0.0347 0.0205 1.0000
14.750 1.3459 0.06409 0.05781 -0.0348 0.0200 1.0000
15.000 1.3403 0.06784 0.06164 -0.0351 0.0196 1.0000
15.250 1.3307 0.07219 0.06608 -0.0355 0.0190 1.0000
15.500 1.3215 0.07662 0.07059 -0.0361 0.0187 1.0000
15.750 1.3114 0.08121 0.07527 -0.0367 0.0184 1.0000
16.000 1.3086 0.08489 0.07904 -0.0373 0.0183 1.0000
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