GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 100,000 Max Cl/Cd: 59.03 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe144-il-100000.txt Download as CSV file: xf-goe144-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 144 (MVA H.21) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3472 0.10628 0.10150 -0.0268 1.0000 0.0801
-8.000 -0.3614 0.10601 0.10136 -0.0274 1.0000 0.0804
-7.750 -0.3675 0.10487 0.10032 -0.0311 1.0000 0.0806
-7.500 -0.3330 0.09499 0.09034 -0.0239 1.0000 0.0836
-7.250 -0.3321 0.09255 0.08796 -0.0225 1.0000 0.0853
-7.000 -0.3356 0.09051 0.08600 -0.0211 1.0000 0.0872
-6.750 -0.3383 0.08832 0.08389 -0.0208 1.0000 0.0895
-6.500 -0.3418 0.08638 0.08202 -0.0219 1.0000 0.0919
-6.250 -0.3438 0.08560 0.08126 -0.0313 1.0000 0.0939
-6.000 -0.3411 0.08133 0.07706 -0.0294 1.0000 0.0948
-5.750 -0.3379 0.07795 0.07374 -0.0238 1.0000 0.0968
-5.500 -0.3328 0.07553 0.07135 -0.0224 1.0000 0.1011
-5.250 -0.3131 0.07280 0.06848 -0.0349 1.0000 0.1074
-5.000 -0.3133 0.06917 0.06497 -0.0293 1.0000 0.1089
-4.750 -0.3070 0.06651 0.06234 -0.0272 1.0000 0.1117
-4.250 -0.2736 0.06005 0.05575 -0.0341 1.0000 0.1222
-4.000 -0.2663 0.05771 0.05343 -0.0321 1.0000 0.1259
-3.750 -0.2425 0.05469 0.05025 -0.0370 1.0000 0.1359
-3.500 -0.2357 0.05260 0.04822 -0.0350 1.0000 0.1402
-3.250 -0.1809 0.04810 0.04346 -0.0445 0.9926 0.1518
-3.000 -0.1021 0.03687 0.03089 -0.0594 0.9880 0.1071
-2.750 -0.0578 0.03295 0.02682 -0.0640 0.9806 0.1038
-2.500 -0.0065 0.02796 0.02085 -0.0693 0.9739 0.1064
-2.250 0.0385 0.02610 0.01879 -0.0731 0.9637 0.1127
-2.000 0.0864 0.02407 0.01630 -0.0769 0.9546 0.1248
-1.750 0.1349 0.02295 0.01481 -0.0807 0.9448 0.1500
-1.500 0.1784 0.02216 0.01394 -0.0837 0.9324 0.1696
-1.250 0.2218 0.02186 0.01364 -0.0868 0.9200 0.1958
-1.000 0.2674 0.02096 0.01250 -0.0899 0.9090 0.2077
-0.750 0.3204 0.01998 0.01136 -0.0942 0.9019 0.2185
-0.500 0.3622 0.01915 0.01052 -0.0964 0.8890 0.2294
-0.250 0.4030 0.01835 0.00966 -0.0983 0.8754 0.2425
0.000 0.4416 0.01765 0.00893 -0.0997 0.8610 0.2609
0.250 0.4783 0.01696 0.00830 -0.1008 0.8456 0.2817
0.500 0.5125 0.01638 0.00774 -0.1013 0.8298 0.3040
0.750 0.5437 0.01588 0.00731 -0.1014 0.8121 0.3291
1.000 0.5739 0.01539 0.00693 -0.1013 0.7941 0.3647
1.250 0.6173 0.01356 0.00652 -0.1036 0.7761 1.0000
1.500 0.6483 0.01358 0.00618 -0.1032 0.7577 1.0000
1.750 0.6750 0.01377 0.00615 -0.1023 0.7379 1.0000
2.000 0.7022 0.01401 0.00620 -0.1017 0.7203 1.0000
2.250 0.7289 0.01431 0.00636 -0.1011 0.7040 1.0000
2.500 0.7551 0.01465 0.00657 -0.1004 0.6885 1.0000
2.750 0.7808 0.01501 0.00683 -0.0997 0.6735 1.0000
3.000 0.8061 0.01537 0.00712 -0.0990 0.6589 1.0000
3.250 0.8311 0.01574 0.00746 -0.0982 0.6445 1.0000
3.500 0.8559 0.01610 0.00778 -0.0973 0.6302 1.0000
3.750 0.8806 0.01646 0.00812 -0.0965 0.6159 1.0000
4.000 0.9050 0.01681 0.00844 -0.0956 0.6012 1.0000
4.250 0.9293 0.01712 0.00875 -0.0945 0.5855 1.0000
4.500 0.9535 0.01739 0.00899 -0.0934 0.5691 1.0000
4.750 0.9774 0.01765 0.00920 -0.0923 0.5520 1.0000
5.000 1.0000 0.01795 0.00954 -0.0910 0.5341 1.0000
5.250 1.0229 0.01823 0.00988 -0.0898 0.5163 1.0000
5.500 1.0460 0.01851 0.01017 -0.0886 0.4985 1.0000
5.750 1.0692 0.01881 0.01047 -0.0874 0.4812 1.0000
6.000 1.0916 0.01910 0.01080 -0.0861 0.4629 1.0000
6.250 1.1119 0.01928 0.01106 -0.0844 0.4404 1.0000
6.500 1.1306 0.01934 0.01114 -0.0824 0.4141 1.0000
6.750 1.1493 0.01951 0.01132 -0.0805 0.3883 1.0000
7.000 1.1683 0.01979 0.01162 -0.0787 0.3639 1.0000
7.250 1.1857 0.02011 0.01195 -0.0768 0.3344 1.0000
7.500 1.2028 0.02054 0.01243 -0.0748 0.3023 1.0000
7.750 1.2177 0.02118 0.01294 -0.0727 0.2642 1.0000
8.000 1.2334 0.02197 0.01366 -0.0707 0.2271 1.0000
8.250 1.2449 0.02317 0.01460 -0.0682 0.1638 1.0000
8.500 1.2474 0.02535 0.01614 -0.0649 0.0958 1.0000
8.750 1.2540 0.02719 0.01779 -0.0619 0.0643 1.0000
9.000 1.2624 0.02874 0.01931 -0.0591 0.0542 1.0000
9.250 1.2681 0.03033 0.02096 -0.0560 0.0501 1.0000
9.500 1.2719 0.03182 0.02260 -0.0526 0.0477 1.0000
9.750 1.2739 0.03343 0.02435 -0.0493 0.0460 1.0000
10.000 1.2746 0.03521 0.02623 -0.0461 0.0445 1.0000
10.250 1.2742 0.03722 0.02831 -0.0432 0.0431 1.0000
10.500 1.2735 0.03963 0.03072 -0.0405 0.0415 1.0000
10.750 1.2811 0.04157 0.03282 -0.0385 0.0403 1.0000
11.000 1.2926 0.04367 0.03504 -0.0368 0.0393 1.0000
11.250 1.3099 0.04599 0.03750 -0.0354 0.0388 1.0000
11.500 1.3300 0.04870 0.04045 -0.0343 0.0385 1.0000
11.750 1.3477 0.05187 0.04389 -0.0332 0.0386 1.0000
12.000 1.3566 0.05544 0.04779 -0.0317 0.0389 1.0000
12.250 1.3572 0.05915 0.05183 -0.0301 0.0393 1.0000
12.500 1.3517 0.06306 0.05606 -0.0285 0.0397 1.0000
12.750 1.3419 0.06717 0.06047 -0.0273 0.0400 1.0000
13.000 1.3290 0.07158 0.06515 -0.0266 0.0403 1.0000
13.250 1.3137 0.07636 0.07019 -0.0267 0.0405 1.0000
13.500 1.2969 0.08151 0.07558 -0.0275 0.0408 1.0000
13.750 1.2784 0.08713 0.08142 -0.0291 0.0410 1.0000
14.000 1.2594 0.09333 0.08782 -0.0313 0.0413 1.0000
14.250 1.2420 0.09993 0.09459 -0.0340 0.0416 1.0000
14.500 1.2215 0.10647 0.10135 -0.0377 0.0419 1.0000
14.750 1.1931 0.11454 0.10968 -0.0438 0.0425 1.0000
15.000 1.1500 0.12745 0.12284 -0.0539 0.0433 1.0000
15.250 1.0554 0.16175 0.15715 -0.0779 0.0475 1.0000
15.500 1.0492 0.17006 0.16542 -0.0819 0.0494 1.0000
15.750 1.0527 0.17477 0.17013 -0.0833 0.0507 1.0000
16.000 1.0372 0.19059 0.18587 -0.0916 0.0631 1.0000
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Polar data table (+)
Polar graphs
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