GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 200,000 Max Cl/Cd: 75.39 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795-il-200000.txt Download as CSV file: xf-goe795-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4634 0.13110 0.12727 -0.0167 1.0000 0.0371
-11.250 -0.4693 0.12891 0.12513 -0.0211 1.0000 0.0383
-11.000 -0.4683 0.12561 0.12187 -0.0233 1.0000 0.0385
-10.750 -0.4658 0.12194 0.11822 -0.0248 1.0000 0.0386
-10.500 -0.4652 0.11516 0.11148 -0.0240 1.0000 0.0399
-10.250 -0.4538 0.11205 0.10836 -0.0222 1.0000 0.0414
-10.000 -0.4482 0.10904 0.10536 -0.0222 1.0000 0.0435
-9.750 -0.4454 0.10594 0.10228 -0.0230 1.0000 0.0464
-9.500 -0.4468 0.10257 0.09894 -0.0252 1.0000 0.0492
-9.250 -0.3850 0.08864 0.08534 -0.0341 1.0000 0.0522
-9.000 -0.3708 0.08569 0.08236 -0.0313 1.0000 0.0538
-8.750 -0.3669 0.08260 0.07930 -0.0307 1.0000 0.0554
-8.500 -0.3673 0.07926 0.07595 -0.0309 1.0000 0.0571
-8.250 -0.4707 0.08374 0.08040 -0.0329 1.0000 0.0530
-8.000 -0.4673 0.08140 0.07809 -0.0311 1.0000 0.0542
-7.750 -0.4706 0.07883 0.07556 -0.0304 1.0000 0.0554
-7.500 -0.4726 0.07568 0.07244 -0.0311 1.0000 0.0569
-7.250 -0.4758 0.07215 0.06893 -0.0324 1.0000 0.0589
-7.000 -0.4793 0.06809 0.06485 -0.0345 1.0000 0.0610
-6.750 -0.4905 0.06291 0.05923 -0.0400 1.0000 0.0639
-6.500 -0.4909 0.05733 0.05379 -0.0385 1.0000 0.0652
-6.250 -0.4833 0.05569 0.05224 -0.0357 1.0000 0.0667
-6.000 -0.4759 0.05427 0.05080 -0.0335 1.0000 0.0698
-5.500 -0.4520 0.03578 0.03222 -0.0310 1.0000 0.0788
-5.250 -0.4409 0.03339 0.02982 -0.0300 0.9993 0.0804
-5.000 -0.4537 0.03224 0.02702 -0.0293 1.0000 0.0531
-4.750 -0.4393 0.02867 0.02321 -0.0273 1.0000 0.0454
-4.500 -0.4093 0.02375 0.01717 -0.0271 0.9972 0.0395
-4.250 -0.3731 0.02204 0.01509 -0.0288 0.9934 0.0390
-4.000 -0.3402 0.01984 0.01250 -0.0299 0.9891 0.0393
-3.750 -0.3062 0.01773 0.01014 -0.0311 0.9853 0.0415
-3.500 -0.2681 0.01672 0.00906 -0.0333 0.9818 0.0451
-3.250 -0.2349 0.01593 0.00811 -0.0343 0.9752 0.0508
-3.000 -0.1980 0.01499 0.00724 -0.0362 0.9707 0.0662
-2.750 -0.1634 0.01456 0.00683 -0.0377 0.9644 0.0861
-2.500 -0.1271 0.01397 0.00630 -0.0395 0.9589 0.1116
-2.250 -0.0902 0.01347 0.00594 -0.0416 0.9541 0.1509
-2.000 -0.0570 0.01312 0.00577 -0.0429 0.9469 0.1985
-1.750 -0.0183 0.01256 0.00551 -0.0454 0.9432 0.2714
-1.500 0.0066 0.01169 0.00539 -0.0452 0.9348 0.4471
-1.250 0.1202 0.01045 0.00562 -0.0629 0.9504 1.0000
-1.000 0.1645 0.01032 0.00534 -0.0662 0.9451 1.0000
-0.750 0.2098 0.01011 0.00500 -0.0697 0.9392 1.0000
-0.500 0.2554 0.00986 0.00466 -0.0732 0.9321 1.0000
-0.250 0.2979 0.00962 0.00434 -0.0760 0.9237 1.0000
0.000 0.3402 0.00938 0.00404 -0.0787 0.9159 1.0000
0.250 0.3731 0.00928 0.00388 -0.0796 0.9047 1.0000
0.500 0.4055 0.00919 0.00376 -0.0804 0.8940 1.0000
0.750 0.4374 0.00912 0.00366 -0.0810 0.8833 1.0000
1.000 0.4679 0.00907 0.00357 -0.0813 0.8719 1.0000
1.250 0.4964 0.00905 0.00351 -0.0812 0.8595 1.0000
1.500 0.5219 0.00906 0.00348 -0.0803 0.8445 1.0000
1.750 0.5459 0.00906 0.00346 -0.0791 0.8262 1.0000
2.000 0.5710 0.00905 0.00337 -0.0780 0.8062 1.0000
2.250 0.5942 0.00910 0.00336 -0.0766 0.7852 1.0000
2.500 0.6182 0.00917 0.00339 -0.0754 0.7665 1.0000
2.750 0.6418 0.00927 0.00344 -0.0742 0.7470 1.0000
3.000 0.6645 0.00939 0.00355 -0.0728 0.7259 1.0000
3.250 0.6871 0.00953 0.00364 -0.0714 0.7037 1.0000
3.500 0.7091 0.00968 0.00373 -0.0698 0.6789 1.0000
3.750 0.7300 0.00983 0.00384 -0.0680 0.6498 1.0000
4.000 0.7504 0.01000 0.00396 -0.0662 0.6164 1.0000
4.250 0.7705 0.01022 0.00413 -0.0643 0.5789 1.0000
4.500 0.7888 0.01054 0.00428 -0.0621 0.5290 1.0000
4.750 0.8063 0.01095 0.00450 -0.0599 0.4754 1.0000
5.000 0.8229 0.01148 0.00479 -0.0576 0.4215 1.0000
5.250 0.8393 0.01207 0.00517 -0.0553 0.3712 1.0000
5.500 0.8554 0.01272 0.00562 -0.0531 0.3201 1.0000
5.750 0.8702 0.01351 0.00616 -0.0507 0.2443 1.0000
6.000 0.8788 0.01491 0.00695 -0.0475 0.1495 1.0000
6.250 0.8922 0.01602 0.00783 -0.0450 0.1138 1.0000
6.500 0.9090 0.01683 0.00859 -0.0429 0.0991 1.0000
6.750 0.9265 0.01757 0.00929 -0.0412 0.0876 1.0000
7.000 0.9442 0.01827 0.00996 -0.0396 0.0763 1.0000
7.250 0.9640 0.01881 0.01061 -0.0381 0.0675 1.0000
7.500 0.9805 0.01963 0.01141 -0.0364 0.0538 1.0000
7.750 0.9890 0.02146 0.01332 -0.0330 0.0367 1.0000
8.000 1.0012 0.02292 0.01477 -0.0305 0.0290 1.0000
8.250 1.0202 0.02347 0.01542 -0.0289 0.0231 1.0000
8.500 1.0306 0.02576 0.01773 -0.0263 0.0208 1.0000
8.750 1.0484 0.02742 0.01957 -0.0245 0.0198 1.0000
9.000 1.0665 0.02961 0.02199 -0.0229 0.0190 1.0000
9.250 1.0834 0.03216 0.02483 -0.0212 0.0184 1.0000
9.500 1.0968 0.03510 0.02813 -0.0190 0.0182 1.0000
9.750 1.1045 0.03847 0.03191 -0.0163 0.0182 1.0000
10.000 1.1067 0.04185 0.03568 -0.0131 0.0184 1.0000
10.250 1.1038 0.04517 0.03937 -0.0095 0.0183 1.0000
10.500 1.0956 0.04817 0.04267 -0.0054 0.0183 1.0000
10.750 1.0847 0.05066 0.04542 -0.0013 0.0176 1.0000
11.000 1.0721 0.05340 0.04844 0.0020 0.0173 1.0000
11.250 1.0575 0.05648 0.05174 0.0045 0.0170 1.0000
11.500 1.0327 0.06136 0.05685 0.0061 0.0179 1.0000
11.750 1.0139 0.06561 0.06130 0.0062 0.0178 1.0000
12.000 0.9898 0.07148 0.06733 0.0049 0.0191 1.0000
12.250 0.9680 0.07744 0.07345 0.0023 0.0193 1.0000
12.500 0.9460 0.08442 0.08052 -0.0011 0.0202 1.0000
12.750 0.9239 0.09228 0.08856 -0.0070 0.0197 1.0000
13.000 0.8073 0.09608 0.09257 -0.0053 0.0204 1.0000
13.250 0.7822 0.10508 0.10164 -0.0104 0.0207 1.0000
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