GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.18 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe311-il-1000000.txt Download as CSV file: xf-goe311-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 311 (MVA H.43) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3327 0.11132 0.10981 -0.0166 0.9680 0.0115
-9.500 -0.2371 0.09327 0.09172 -0.0277 0.9079 0.0133
-7.750 -0.3809 0.03257 0.02993 -0.0743 0.8628 0.0095
-7.500 -0.3657 0.02082 0.01731 -0.0796 0.8466 0.0096
-7.250 -0.3441 0.01633 0.01225 -0.0805 0.8271 0.0101
-7.000 -0.3187 0.01500 0.01064 -0.0804 0.8057 0.0105
-6.750 -0.2923 0.01410 0.00951 -0.0804 0.7855 0.0109
-6.500 -0.2653 0.01334 0.00854 -0.0803 0.7683 0.0114
-6.250 -0.2380 0.01267 0.00765 -0.0803 0.7534 0.0118
-6.000 -0.2104 0.01211 0.00690 -0.0802 0.7403 0.0123
-5.750 -0.1824 0.01166 0.00630 -0.0802 0.7284 0.0127
-5.500 -0.1547 0.01090 0.00534 -0.0802 0.7173 0.0138
-5.000 -0.0984 0.01006 0.00424 -0.0802 0.6936 0.0165
-4.750 -0.0700 0.00968 0.00375 -0.0802 0.6799 0.0191
-4.500 -0.0417 0.00944 0.00356 -0.0802 0.6628 0.0292
-4.250 -0.0127 0.00977 0.00386 -0.0803 0.6387 0.0355
-4.000 0.0159 0.00996 0.00397 -0.0803 0.6053 0.0388
-3.750 0.0444 0.01021 0.00410 -0.0804 0.5789 0.0413
-3.500 0.0731 0.01043 0.00423 -0.0805 0.5639 0.0432
-3.250 0.1019 0.01067 0.00440 -0.0806 0.5542 0.0441
-3.000 0.1297 0.01009 0.00367 -0.0806 0.5470 0.0463
-2.750 0.1579 0.00986 0.00339 -0.0807 0.5411 0.0481
-2.500 0.1863 0.00971 0.00321 -0.0808 0.5364 0.0497
-2.250 0.2147 0.00959 0.00304 -0.0809 0.5322 0.0511
-2.000 0.2431 0.00951 0.00290 -0.0809 0.5281 0.0527
-1.750 0.2716 0.00936 0.00272 -0.0810 0.5250 0.0534
-1.500 0.3001 0.00921 0.00253 -0.0810 0.5220 0.0537
-1.250 0.3286 0.00910 0.00237 -0.0811 0.5190 0.0539
-1.000 0.3570 0.00901 0.00224 -0.0811 0.5158 0.0543
-0.750 0.3853 0.00897 0.00214 -0.0812 0.5123 0.0547
-0.500 0.4139 0.00887 0.00204 -0.0813 0.5101 0.0551
-0.250 0.4425 0.00880 0.00197 -0.0813 0.5066 0.0556
0.000 0.4709 0.00872 0.00184 -0.0814 0.5025 0.0580
0.250 0.4991 0.00871 0.00179 -0.0814 0.4981 0.0604
0.500 0.5276 0.00866 0.00175 -0.0815 0.4950 0.0633
0.750 0.5562 0.00860 0.00171 -0.0816 0.4918 0.0668
1.000 0.5845 0.00851 0.00172 -0.0818 0.4883 0.0992
1.250 0.6129 0.00854 0.00178 -0.0819 0.4844 0.1158
1.500 0.6412 0.00858 0.00183 -0.0820 0.4805 0.1241
1.750 0.6699 0.00857 0.00186 -0.0821 0.4761 0.1309
2.000 0.6983 0.00861 0.00188 -0.0822 0.4710 0.1346
2.250 0.7265 0.00865 0.00193 -0.0823 0.4663 0.1400
2.500 0.7551 0.00865 0.00197 -0.0825 0.4628 0.1448
2.750 0.7835 0.00867 0.00202 -0.0826 0.4591 0.1477
3.000 0.8117 0.00868 0.00205 -0.0828 0.4552 0.1534
3.250 0.8398 0.00873 0.00211 -0.0829 0.4512 0.1586
3.500 0.8683 0.00874 0.00216 -0.0831 0.4472 0.1622
3.750 0.8965 0.00874 0.00221 -0.0832 0.4422 0.1702
4.000 0.9245 0.00880 0.00228 -0.0833 0.4370 0.1794
4.250 0.9528 0.00878 0.00236 -0.0835 0.4315 0.2026
4.500 0.9806 0.00874 0.00251 -0.0837 0.4245 0.2926
4.750 1.0044 0.00747 0.00270 -0.0831 0.4175 0.9942
5.000 1.0336 0.00759 0.00277 -0.0835 0.4046 1.0000
5.250 1.0600 0.00784 0.00289 -0.0834 0.3773 1.0000
5.500 1.0855 0.00822 0.00310 -0.0832 0.3434 1.0000
5.750 1.1098 0.00874 0.00341 -0.0829 0.3045 1.0000
6.000 1.1328 0.00941 0.00382 -0.0825 0.2570 1.0000
6.250 1.1555 0.01010 0.00427 -0.0819 0.2130 1.0000
6.500 1.1787 0.01069 0.00468 -0.0815 0.1822 1.0000
6.750 1.2015 0.01130 0.00511 -0.0810 0.1530 1.0000
7.000 1.2191 0.01245 0.00589 -0.0798 0.0877 1.0000
7.250 1.2422 0.01294 0.00634 -0.0793 0.0774 1.0000
7.500 1.2657 0.01337 0.00676 -0.0788 0.0682 1.0000
7.750 1.2813 0.01456 0.00766 -0.0772 0.0197 1.0000
8.000 1.3025 0.01515 0.00826 -0.0763 0.0153 1.0000
8.250 1.3244 0.01563 0.00879 -0.0756 0.0139 1.0000
8.500 1.3456 0.01614 0.00935 -0.0748 0.0129 1.0000
8.750 1.3654 0.01674 0.01000 -0.0737 0.0119 1.0000
9.000 1.3820 0.01757 0.01089 -0.0722 0.0109 1.0000
9.250 1.3976 0.01840 0.01181 -0.0706 0.0103 1.0000
9.500 1.4156 0.01897 0.01242 -0.0693 0.0099 1.0000
9.750 1.4308 0.01962 0.01313 -0.0676 0.0094 1.0000
10.000 1.4421 0.02037 0.01394 -0.0653 0.0089 1.0000
10.250 1.4523 0.02125 0.01488 -0.0631 0.0086 1.0000
10.500 1.4611 0.02230 0.01599 -0.0609 0.0082 1.0000
10.750 1.4664 0.02367 0.01743 -0.0586 0.0079 1.0000
11.000 1.4635 0.02579 0.01967 -0.0558 0.0076 1.0000
11.250 1.4564 0.02847 0.02249 -0.0532 0.0074 1.0000
11.500 1.4653 0.02996 0.02406 -0.0522 0.0072 1.0000
11.750 1.4712 0.03181 0.02599 -0.0512 0.0071 1.0000
12.000 1.4762 0.03387 0.02814 -0.0504 0.0070 1.0000
12.250 1.4791 0.03621 0.03057 -0.0496 0.0068 1.0000
12.500 1.4807 0.03876 0.03320 -0.0490 0.0067 1.0000
12.750 1.4812 0.04148 0.03601 -0.0485 0.0065 1.0000
13.000 1.4816 0.04424 0.03886 -0.0480 0.0064 1.0000
13.250 1.4823 0.04702 0.04172 -0.0477 0.0062 1.0000
13.500 1.4826 0.04992 0.04469 -0.0475 0.0060 1.0000
13.750 1.4832 0.05282 0.04767 -0.0475 0.0059 1.0000
14.000 1.4832 0.05589 0.05082 -0.0475 0.0057 1.0000
14.250 1.4819 0.05919 0.05418 -0.0477 0.0056 1.0000
14.500 1.4786 0.06274 0.05781 -0.0479 0.0055 1.0000
14.750 1.4733 0.06655 0.06170 -0.0481 0.0054 1.0000
15.000 1.4658 0.07063 0.06587 -0.0482 0.0053 1.0000
15.250 1.4537 0.07507 0.07039 -0.0479 0.0051 1.0000
15.500 1.4445 0.07891 0.07432 -0.0471 0.0050 1.0000
15.750 1.4436 0.08245 0.07796 -0.0477 0.0050 1.0000
16.000 1.4422 0.08610 0.08170 -0.0484 0.0049 1.0000
16.250 1.4402 0.08974 0.08544 -0.0489 0.0049 1.0000
16.500 1.4373 0.09356 0.08936 -0.0496 0.0048 1.0000
16.750 1.4341 0.09746 0.09336 -0.0503 0.0048 1.0000
17.000 1.4308 0.10144 0.09744 -0.0512 0.0047 1.0000
17.250 1.4264 0.10561 0.10172 -0.0521 0.0046 1.0000
17.500 1.4217 0.10987 0.10608 -0.0532 0.0046 1.0000
17.750 1.4169 0.11426 0.11059 -0.0545 0.0045 1.0000
18.000 1.4109 0.11889 0.11534 -0.0559 0.0045 1.0000
18.250 1.4046 0.12369 0.12027 -0.0576 0.0044 1.0000
18.500 1.3980 0.12865 0.12535 -0.0595 0.0044 1.0000
18.750 1.3905 0.13384 0.13065 -0.0617 0.0044 1.0000
19.000 1.3827 0.13925 0.13619 -0.0641 0.0043 1.0000
19.250 1.3739 0.14500 0.14207 -0.0669 0.0043 1.0000
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