GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il) Reynolds number: 200,000 Max Cl/Cd: 82.42 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe311-il-200000.txt Download as CSV file: xf-goe311-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2755 0.09856 0.09540 -0.0297 1.0000 0.0428
-8.000 -0.2816 0.09724 0.09417 -0.0316 1.0000 0.0435
-7.750 -0.3010 0.09697 0.09401 -0.0288 1.0000 0.0437
-7.500 -0.2911 0.09398 0.09105 -0.0361 0.9946 0.0440
-7.250 -0.2598 0.08863 0.08565 -0.0469 0.9869 0.0442
-7.000 -0.2368 0.08153 0.07855 -0.0530 0.9825 0.0447
-6.750 -0.2197 0.07774 0.07477 -0.0502 0.9773 0.0464
-6.500 -0.1911 0.07393 0.07093 -0.0548 0.9707 0.0489
-6.250 -0.1647 0.06982 0.06678 -0.0610 0.9589 0.0512
-6.000 -0.1252 0.06526 0.06202 -0.0743 0.9435 0.0552
-5.750 -0.0999 0.06112 0.05773 -0.0789 0.9289 0.0556
-5.500 -0.0936 0.05620 0.05282 -0.0782 0.9147 0.0568
-5.250 -0.0813 0.05411 0.05071 -0.0762 0.9001 0.0584
-5.000 -0.0640 0.05205 0.04858 -0.0759 0.8851 0.0627
-4.750 -0.0372 0.04779 0.04410 -0.0800 0.8702 0.0700
-4.500 -0.0198 0.04608 0.04232 -0.0788 0.8546 0.0743
-4.250 0.0071 0.04253 0.03852 -0.0812 0.8387 0.0827
-4.000 0.0410 0.03176 0.02706 -0.0861 0.8260 0.0649
-3.750 0.0538 0.03830 0.03394 -0.0814 0.8037 0.1003
-3.500 0.0845 0.03402 0.02923 -0.0834 0.7876 0.1020
-3.250 0.1178 0.02451 0.01870 -0.0862 0.7751 0.0866
-3.000 0.1454 0.02100 0.01448 -0.0863 0.7591 0.0903
-2.750 0.1725 0.01872 0.01157 -0.0861 0.7429 0.0914
-2.500 0.1998 0.01734 0.00972 -0.0858 0.7274 0.0919
-2.250 0.2271 0.01630 0.00835 -0.0856 0.7132 0.0929
-2.000 0.2545 0.01570 0.00758 -0.0854 0.7008 0.0945
-1.750 0.2820 0.01546 0.00721 -0.0852 0.6899 0.0971
-1.500 0.3101 0.01513 0.00674 -0.0851 0.6787 0.1004
-1.250 0.3381 0.01471 0.00615 -0.0849 0.6694 0.1037
-1.000 0.3659 0.01438 0.00573 -0.0847 0.6617 0.1077
-0.750 0.3940 0.01424 0.00558 -0.0847 0.6535 0.1142
-0.500 0.4219 0.01410 0.00538 -0.0845 0.6468 0.1246
-0.250 0.4501 0.01408 0.00535 -0.0845 0.6399 0.1428
0.000 0.4781 0.01414 0.00532 -0.0845 0.6338 0.1601
0.250 0.5059 0.01419 0.00535 -0.0845 0.6282 0.1730
0.500 0.5337 0.01421 0.00538 -0.0845 0.6220 0.1837
0.750 0.5615 0.01427 0.00534 -0.0845 0.6172 0.1930
1.000 0.5893 0.01425 0.00538 -0.0846 0.6116 0.1987
1.250 0.6171 0.01428 0.00537 -0.0846 0.6063 0.2044
1.500 0.6447 0.01429 0.00533 -0.0845 0.6018 0.2095
1.750 0.6723 0.01432 0.00544 -0.0845 0.5965 0.2158
2.000 0.6999 0.01436 0.00551 -0.0845 0.5914 0.2249
2.250 0.7276 0.01448 0.00559 -0.0845 0.5872 0.2365
2.500 0.7549 0.01452 0.00576 -0.0846 0.5818 0.2471
2.750 0.7823 0.01455 0.00585 -0.0845 0.5766 0.2566
3.000 0.8093 0.01459 0.00590 -0.0843 0.5707 0.2687
3.250 0.8357 0.01456 0.00596 -0.0841 0.5622 0.2896
3.500 0.8613 0.01434 0.00600 -0.0837 0.5530 0.3851
3.750 0.8943 0.01337 0.00593 -0.0844 0.5430 1.0000
4.000 0.9203 0.01354 0.00610 -0.0840 0.5345 1.0000
4.250 0.9471 0.01378 0.00625 -0.0838 0.5288 1.0000
4.500 0.9735 0.01401 0.00653 -0.0836 0.5229 1.0000
4.750 1.0000 0.01422 0.00675 -0.0834 0.5166 1.0000
5.000 1.0266 0.01449 0.00697 -0.0833 0.5109 1.0000
5.250 1.0525 0.01467 0.00724 -0.0830 0.5036 1.0000
5.500 1.0792 0.01491 0.00745 -0.0828 0.4976 1.0000
5.750 1.1046 0.01509 0.00776 -0.0825 0.4902 1.0000
6.000 1.1310 0.01528 0.00796 -0.0822 0.4836 1.0000
6.250 1.1564 0.01547 0.00828 -0.0819 0.4760 1.0000
6.500 1.1822 0.01560 0.00844 -0.0816 0.4682 1.0000
6.750 1.2066 0.01565 0.00862 -0.0810 0.4569 1.0000
7.000 1.2306 0.01561 0.00865 -0.0803 0.4427 1.0000
7.250 1.2542 0.01557 0.00870 -0.0796 0.4258 1.0000
7.500 1.2776 0.01564 0.00882 -0.0788 0.4085 1.0000
7.750 1.3006 0.01578 0.00905 -0.0781 0.3867 1.0000
8.000 1.3202 0.01612 0.00926 -0.0769 0.3520 1.0000
8.250 1.3376 0.01676 0.00976 -0.0754 0.3137 1.0000
8.500 1.3523 0.01767 0.01048 -0.0737 0.2741 1.0000
8.750 1.3612 0.01901 0.01149 -0.0713 0.2226 1.0000
9.000 1.3672 0.02056 0.01271 -0.0686 0.1700 1.0000
9.250 1.3597 0.02296 0.01450 -0.0644 0.0901 1.0000
9.500 1.3580 0.02466 0.01611 -0.0605 0.0670 1.0000
9.750 1.3563 0.02650 0.01778 -0.0572 0.0395 1.0000
10.000 1.3582 0.02824 0.01952 -0.0545 0.0336 1.0000
10.250 1.3615 0.02999 0.02143 -0.0524 0.0311 1.0000
10.500 1.3615 0.03213 0.02369 -0.0503 0.0290 1.0000
10.750 1.3583 0.03474 0.02643 -0.0486 0.0273 1.0000
11.000 1.3547 0.03758 0.02942 -0.0473 0.0264 1.0000
11.250 1.3536 0.04034 0.03234 -0.0463 0.0258 1.0000
11.500 1.3511 0.04334 0.03549 -0.0455 0.0253 1.0000
11.750 1.3479 0.04650 0.03877 -0.0449 0.0249 1.0000
12.000 1.3445 0.04972 0.04212 -0.0443 0.0244 1.0000
12.250 1.3414 0.05292 0.04543 -0.0437 0.0241 1.0000
12.500 1.3390 0.05605 0.04865 -0.0430 0.0237 1.0000
12.750 1.3379 0.05900 0.05170 -0.0423 0.0234 1.0000
13.000 1.3383 0.06174 0.05452 -0.0414 0.0230 1.0000
13.250 1.3400 0.06435 0.05721 -0.0405 0.0225 1.0000
13.500 1.3426 0.06683 0.05974 -0.0395 0.0218 1.0000
13.750 1.3475 0.06890 0.06181 -0.0380 0.0210 1.0000
14.000 1.3609 0.06994 0.06284 -0.0349 0.0204 1.0000
14.250 1.3773 0.07130 0.06430 -0.0322 0.0202 1.0000
14.500 1.3889 0.07357 0.06675 -0.0306 0.0201 1.0000
14.750 1.3949 0.07639 0.06975 -0.0296 0.0201 1.0000
15.000 1.3967 0.07956 0.07311 -0.0292 0.0202 1.0000
15.250 1.3951 0.08307 0.07683 -0.0292 0.0204 1.0000
15.500 1.3904 0.08694 0.08095 -0.0297 0.0206 1.0000
15.750 1.3823 0.09134 0.08561 -0.0307 0.0209 1.0000
16.000 1.3704 0.09655 0.09112 -0.0321 0.0213 1.0000
16.250 1.3530 0.10297 0.09790 -0.0342 0.0220 1.0000
16.500 1.3317 0.11033 0.10559 -0.0373 0.0226 1.0000
16.750 1.3110 0.11786 0.11341 -0.0407 0.0232 1.0000
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Polar data table (+)
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