GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 438 AIRFOIL (goe438-il) Reynolds number: 100,000 Max Cl/Cd: 52.32 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe438-il-100000-n5.txt Download as CSV file: xf-goe438-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 438 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3501 0.09353 0.08839 -0.0371 1.0000 0.0678
-8.750 -0.3563 0.09054 0.08547 -0.0375 1.0000 0.0689
-8.500 -0.3648 0.08760 0.08260 -0.0374 1.0000 0.0690
-8.250 -0.3761 0.08481 0.07991 -0.0366 1.0000 0.0682
-8.000 -0.3940 0.08230 0.07750 -0.0350 1.0000 0.0670
-7.750 -0.4139 0.07926 0.07455 -0.0342 1.0000 0.0657
-7.500 -0.4313 0.07576 0.07110 -0.0341 1.0000 0.0649
-7.250 -0.4207 0.07123 0.06651 -0.0390 0.9949 0.0666
-7.000 -0.4019 0.06512 0.06023 -0.0467 0.9865 0.0677
-6.750 -0.3833 0.05896 0.05384 -0.0531 0.9780 0.0675
-6.500 -0.3617 0.05348 0.04805 -0.0585 0.9704 0.0692
-6.250 -0.3403 0.04857 0.04280 -0.0621 0.9623 0.0695
-6.000 -0.3184 0.04433 0.03817 -0.0646 0.9545 0.0695
-5.750 -0.2929 0.04037 0.03373 -0.0670 0.9475 0.0707
-5.500 -0.2688 0.03730 0.03018 -0.0681 0.9398 0.0717
-5.250 -0.2408 0.03466 0.02715 -0.0693 0.9331 0.0719
-5.000 -0.2112 0.03239 0.02447 -0.0706 0.9270 0.0722
-4.750 -0.1841 0.03058 0.02229 -0.0709 0.9189 0.0726
-4.500 -0.1496 0.02863 0.02007 -0.0728 0.9144 0.0740
-4.250 -0.1239 0.02738 0.01870 -0.0728 0.9050 0.0752
-4.000 -0.0889 0.02601 0.01710 -0.0743 0.8994 0.0761
-3.750 -0.0608 0.02487 0.01577 -0.0743 0.8896 0.0767
-3.500 -0.0246 0.02367 0.01437 -0.0757 0.8832 0.0776
-3.250 0.0040 0.02275 0.01328 -0.0756 0.8721 0.0785
-3.000 0.0367 0.02183 0.01223 -0.0763 0.8629 0.0797
-2.750 0.0698 0.02106 0.01131 -0.0769 0.8533 0.0821
-2.500 0.0993 0.02039 0.01052 -0.0769 0.8414 0.0840
-2.250 0.1307 0.01972 0.00973 -0.0771 0.8303 0.0853
-2.000 0.1635 0.01905 0.00897 -0.0776 0.8199 0.0865
-1.750 0.1904 0.01839 0.00834 -0.0772 0.8063 0.0881
-1.500 0.2175 0.01789 0.00787 -0.0767 0.7927 0.0901
-1.250 0.2446 0.01750 0.00747 -0.0763 0.7791 0.0930
-1.000 0.2716 0.01717 0.00711 -0.0758 0.7653 0.0971
-0.750 0.2984 0.01689 0.00676 -0.0752 0.7511 0.1007
-0.500 0.3244 0.01655 0.00643 -0.0746 0.7366 0.1047
-0.250 0.3507 0.01632 0.00615 -0.0739 0.7215 0.1099
0.000 0.3772 0.01611 0.00590 -0.0733 0.7065 0.1172
0.250 0.4038 0.01588 0.00569 -0.0728 0.6913 0.1337
0.500 0.4309 0.01540 0.00550 -0.0725 0.6764 0.2155
1.000 0.5377 0.01357 0.00543 -0.0820 0.6425 1.0000
1.250 0.5614 0.01372 0.00540 -0.0809 0.6276 1.0000
1.500 0.5848 0.01390 0.00541 -0.0798 0.6127 1.0000
1.750 0.6077 0.01410 0.00547 -0.0787 0.5976 1.0000
2.000 0.6306 0.01430 0.00555 -0.0775 0.5825 1.0000
2.250 0.6533 0.01451 0.00565 -0.0764 0.5674 1.0000
2.500 0.6760 0.01472 0.00577 -0.0752 0.5523 1.0000
2.750 0.6987 0.01494 0.00590 -0.0741 0.5373 1.0000
3.000 0.7213 0.01517 0.00604 -0.0729 0.5224 1.0000
3.250 0.7439 0.01541 0.00620 -0.0718 0.5079 1.0000
3.500 0.7666 0.01566 0.00637 -0.0707 0.4940 1.0000
3.750 0.7894 0.01593 0.00655 -0.0697 0.4809 1.0000
4.000 0.8120 0.01621 0.00675 -0.0686 0.4682 1.0000
4.250 0.8347 0.01651 0.00700 -0.0676 0.4556 1.0000
4.500 0.8575 0.01682 0.00727 -0.0666 0.4442 1.0000
4.750 0.8804 0.01716 0.00755 -0.0656 0.4342 1.0000
5.000 0.9032 0.01751 0.00787 -0.0646 0.4237 1.0000
5.250 0.9260 0.01787 0.00821 -0.0637 0.4139 1.0000
5.500 0.9490 0.01825 0.00855 -0.0628 0.4054 1.0000
5.750 0.9718 0.01863 0.00897 -0.0619 0.3963 1.0000
6.000 0.9946 0.01905 0.00932 -0.0610 0.3883 1.0000
6.250 1.0162 0.01943 0.00978 -0.0599 0.3778 1.0000
6.500 1.0370 0.01982 0.01016 -0.0587 0.3666 1.0000
6.750 1.0571 0.02021 0.01051 -0.0574 0.3549 1.0000
7.000 1.0766 0.02060 0.01091 -0.0560 0.3428 1.0000
7.250 1.0964 0.02100 0.01139 -0.0547 0.3320 1.0000
7.500 1.1169 0.02144 0.01183 -0.0535 0.3239 1.0000
7.750 1.1373 0.02188 0.01238 -0.0524 0.3156 1.0000
8.000 1.1576 0.02235 0.01288 -0.0512 0.3086 1.0000
8.250 1.1766 0.02280 0.01346 -0.0498 0.2995 1.0000
8.500 1.1943 0.02327 0.01397 -0.0482 0.2899 1.0000
8.750 1.2111 0.02374 0.01450 -0.0466 0.2800 1.0000
9.000 1.2281 0.02424 0.01515 -0.0450 0.2704 1.0000
9.250 1.2441 0.02477 0.01572 -0.0432 0.2625 1.0000
9.500 1.2601 0.02531 0.01643 -0.0415 0.2534 1.0000
9.750 1.2737 0.02589 0.01708 -0.0394 0.2446 1.0000
10.000 1.2835 0.02649 0.01776 -0.0368 0.2335 1.0000
10.250 1.2935 0.02716 0.01856 -0.0343 0.2216 1.0000
10.500 1.3023 0.02792 0.01940 -0.0318 0.2096 1.0000
10.750 1.3093 0.02880 0.02036 -0.0293 0.1962 1.0000
11.000 1.3148 0.02983 0.02144 -0.0268 0.1816 1.0000
11.250 1.3183 0.03106 0.02270 -0.0243 0.1663 1.0000
11.500 1.3189 0.03257 0.02420 -0.0218 0.1511 1.0000
11.750 1.3175 0.03435 0.02598 -0.0195 0.1376 1.0000
12.000 1.3145 0.03640 0.02805 -0.0174 0.1261 1.0000
12.250 1.3095 0.03877 0.03044 -0.0156 0.1165 1.0000
12.500 1.3037 0.04139 0.03308 -0.0142 0.1081 1.0000
12.750 1.2991 0.04410 0.03587 -0.0132 0.1005 1.0000
13.000 1.2917 0.04725 0.03906 -0.0125 0.0943 1.0000
13.250 1.2868 0.05036 0.04228 -0.0122 0.0885 1.0000
13.500 1.2786 0.05400 0.04598 -0.0123 0.0833 1.0000
13.750 1.2707 0.05779 0.04985 -0.0126 0.0792 1.0000
14.000 1.2625 0.06179 0.05396 -0.0133 0.0754 1.0000
14.250 1.2515 0.06633 0.05855 -0.0143 0.0725 1.0000
14.500 1.2424 0.07074 0.06304 -0.0154 0.0701 1.0000
14.750 1.2352 0.07504 0.06747 -0.0165 0.0676 1.0000
15.000 1.2272 0.07956 0.07209 -0.0178 0.0653 1.0000
15.250 1.2187 0.08419 0.07678 -0.0192 0.0631 1.0000
15.500 1.2127 0.08838 0.08095 -0.0203 0.0608 1.0000
15.750 1.2086 0.09258 0.08533 -0.0217 0.0583 1.0000
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Polar data table (+)
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