GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 100,000 Max Cl/Cd: 56.65 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe122-il-100000-n5.txt Download as CSV file: xf-goe122-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 122 (MVA H.2) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3873 0.09815 0.09346 -0.0097 1.0000 0.0362
-7.750 -0.3817 0.09500 0.09035 -0.0114 1.0000 0.0372
-7.500 -0.3767 0.09189 0.08730 -0.0135 1.0000 0.0382
-7.250 -0.3698 0.08862 0.08408 -0.0166 1.0000 0.0394
-7.000 -0.3588 0.08521 0.08071 -0.0228 1.0000 0.0411
-6.750 -0.3411 0.08161 0.07709 -0.0324 1.0000 0.0420
-6.500 -0.3236 0.07774 0.07314 -0.0383 1.0000 0.0423
-6.250 -0.3181 0.07298 0.06847 -0.0375 1.0000 0.0430
-6.000 -0.3143 0.07023 0.06581 -0.0337 1.0000 0.0451
-5.750 -0.3045 0.06754 0.06314 -0.0343 1.0000 0.0485
-5.500 -0.2759 0.06457 0.05984 -0.0442 1.0000 0.0540
-5.250 -0.2737 0.06036 0.05576 -0.0425 1.0000 0.0550
-5.000 -0.2603 0.05717 0.05262 -0.0421 0.9964 0.0571
-4.750 -0.2001 0.05360 0.04833 -0.0541 0.9864 0.0670
-4.500 -0.1781 0.04793 0.04292 -0.0559 0.9779 0.0698
-4.250 -0.1347 0.04407 0.03870 -0.0622 0.9671 0.0828
-4.000 -0.0922 0.03724 0.03143 -0.0661 0.9565 0.0487
-3.750 -0.0523 0.03294 0.02662 -0.0696 0.9453 0.0465
-3.500 -0.0149 0.02988 0.02312 -0.0721 0.9352 0.0478
-3.250 0.0199 0.02688 0.01955 -0.0735 0.9236 0.0463
-3.000 0.0522 0.02495 0.01722 -0.0743 0.9115 0.0480
-2.750 0.0837 0.02331 0.01517 -0.0747 0.8989 0.0500
-2.500 0.1140 0.02177 0.01324 -0.0747 0.8859 0.0499
-2.250 0.1429 0.02052 0.01164 -0.0744 0.8720 0.0502
-2.000 0.1709 0.01959 0.01043 -0.0739 0.8575 0.0519
-1.750 0.1984 0.01890 0.00948 -0.0733 0.8422 0.0538
-1.500 0.2252 0.01809 0.00851 -0.0726 0.8265 0.0540
-1.250 0.2517 0.01731 0.00764 -0.0719 0.8106 0.0544
-1.000 0.2779 0.01658 0.00687 -0.0712 0.7941 0.0551
-0.750 0.3039 0.01602 0.00626 -0.0705 0.7773 0.0562
-0.500 0.3300 0.01559 0.00576 -0.0697 0.7600 0.0577
-0.250 0.3563 0.01528 0.00537 -0.0691 0.7418 0.0604
0.000 0.3828 0.01508 0.00505 -0.0685 0.7235 0.0655
0.250 0.4092 0.01487 0.00471 -0.0678 0.7053 0.0695
0.500 0.4359 0.01474 0.00444 -0.0671 0.6873 0.0749
0.750 0.4630 0.01462 0.00424 -0.0666 0.6689 0.0877
1.250 0.5176 0.01257 0.00409 -0.0660 0.6334 1.0000
1.500 0.5440 0.01277 0.00408 -0.0655 0.6159 1.0000
1.750 0.5704 0.01298 0.00410 -0.0650 0.5983 1.0000
2.000 0.5968 0.01319 0.00415 -0.0645 0.5801 1.0000
2.250 0.6231 0.01341 0.00424 -0.0642 0.5615 1.0000
2.500 0.6494 0.01364 0.00434 -0.0638 0.5435 1.0000
2.750 0.6757 0.01388 0.00448 -0.0634 0.5267 1.0000
3.000 0.7020 0.01413 0.00463 -0.0630 0.5113 1.0000
3.250 0.7283 0.01439 0.00481 -0.0627 0.4975 1.0000
3.500 0.7545 0.01466 0.00503 -0.0624 0.4839 1.0000
3.750 0.7806 0.01495 0.00526 -0.0620 0.4710 1.0000
4.000 0.8067 0.01525 0.00552 -0.0617 0.4585 1.0000
4.250 0.8325 0.01557 0.00581 -0.0613 0.4463 1.0000
4.500 0.8585 0.01590 0.00614 -0.0610 0.4352 1.0000
4.750 0.8847 0.01622 0.00651 -0.0608 0.4253 1.0000
5.000 0.9105 0.01658 0.00691 -0.0604 0.4158 1.0000
5.250 0.9358 0.01693 0.00728 -0.0600 0.4025 1.0000
5.500 0.9607 0.01726 0.00765 -0.0596 0.3845 1.0000
5.750 0.9853 0.01760 0.00802 -0.0591 0.3646 1.0000
6.000 1.0097 0.01795 0.00844 -0.0587 0.3463 1.0000
6.250 1.0342 0.01832 0.00888 -0.0582 0.3293 1.0000
6.500 1.0586 0.01869 0.00935 -0.0578 0.3094 1.0000
6.750 1.0826 0.01911 0.00985 -0.0573 0.2881 1.0000
7.000 1.1064 0.01957 0.01044 -0.0567 0.2668 1.0000
7.250 1.1288 0.02016 0.01102 -0.0561 0.2355 1.0000
7.500 1.1495 0.02097 0.01173 -0.0553 0.2008 1.0000
7.750 1.1666 0.02227 0.01277 -0.0543 0.1597 1.0000
8.000 1.1816 0.02391 0.01409 -0.0532 0.0844 1.0000
8.250 1.1943 0.02576 0.01573 -0.0517 0.0624 1.0000
8.500 1.2080 0.02738 0.01739 -0.0503 0.0543 1.0000
8.750 1.2220 0.02883 0.01904 -0.0488 0.0491 1.0000
9.000 1.2298 0.03080 0.02112 -0.0469 0.0446 1.0000
9.250 1.2402 0.03235 0.02290 -0.0451 0.0416 1.0000
9.500 1.2476 0.03407 0.02479 -0.0432 0.0383 1.0000
9.750 1.2501 0.03601 0.02688 -0.0408 0.0357 1.0000
10.000 1.2474 0.03834 0.02928 -0.0381 0.0339 1.0000
10.250 1.2497 0.04057 0.03161 -0.0361 0.0323 1.0000
10.500 1.2560 0.04249 0.03373 -0.0346 0.0303 1.0000
10.750 1.2610 0.04464 0.03604 -0.0332 0.0282 1.0000
11.000 1.2664 0.04694 0.03847 -0.0318 0.0268 1.0000
11.250 1.2720 0.04937 0.04099 -0.0305 0.0255 1.0000
11.500 1.2779 0.05200 0.04365 -0.0293 0.0242 1.0000
11.750 1.2838 0.05499 0.04676 -0.0281 0.0229 1.0000
12.000 1.2841 0.05779 0.04987 -0.0275 0.0220 1.0000
12.250 1.2837 0.06096 0.05336 -0.0270 0.0211 1.0000
12.500 1.2821 0.06452 0.05718 -0.0267 0.0206 1.0000
12.750 1.2778 0.06842 0.06135 -0.0267 0.0201 1.0000
13.000 1.2708 0.07271 0.06589 -0.0272 0.0198 1.0000
13.250 1.2615 0.07740 0.07083 -0.0283 0.0195 1.0000
13.500 1.2500 0.08253 0.07621 -0.0299 0.0193 1.0000
13.750 1.2365 0.08812 0.08203 -0.0321 0.0192 1.0000
14.000 1.2213 0.09419 0.08833 -0.0349 0.0191 1.0000
14.250 1.2047 0.10082 0.09518 -0.0383 0.0191 1.0000
14.500 1.1868 0.10809 0.10265 -0.0424 0.0192 1.0000
14.750 1.1678 0.11612 0.11088 -0.0472 0.0193 1.0000
15.000 1.1478 0.12499 0.11993 -0.0528 0.0195 1.0000
15.250 1.1270 0.13474 0.12985 -0.0591 0.0199 1.0000
15.500 1.1054 0.14560 0.14080 -0.0662 0.0202 1.0000
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Polar data table (+)
Polar graphs
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