GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 200,000 Max Cl/Cd: 79.33 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe144-il-200000.txt Download as CSV file: xf-goe144-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3483 0.10017 0.09678 -0.0280 1.0000 0.0445
-8.000 -0.3577 0.09858 0.09528 -0.0278 1.0000 0.0446
-7.750 -0.3639 0.09645 0.09322 -0.0284 1.0000 0.0447
-7.500 -0.3508 0.09069 0.08746 -0.0242 1.0000 0.0460
-7.250 -0.3485 0.08844 0.08525 -0.0220 1.0000 0.0469
-7.000 -0.3509 0.08658 0.08343 -0.0201 1.0000 0.0481
-6.750 -0.3536 0.08455 0.08145 -0.0191 1.0000 0.0496
-6.500 -0.3564 0.08240 0.07934 -0.0187 1.0000 0.0512
-6.250 -0.3577 0.08005 0.07704 -0.0228 1.0000 0.0543
-6.000 -0.3434 0.07659 0.07351 -0.0339 1.0000 0.0554
-5.750 -0.3502 0.07249 0.06950 -0.0278 1.0000 0.0567
-5.500 -0.3464 0.07060 0.06764 -0.0243 1.0000 0.0581
-5.250 -0.3391 0.06819 0.06525 -0.0240 1.0000 0.0600
-5.000 -0.2699 0.06159 0.05828 -0.0455 0.9953 0.0673
-4.750 -0.2461 0.05493 0.05163 -0.0492 0.9906 0.0687
-4.500 -0.2158 0.05197 0.04866 -0.0515 0.9857 0.0710
-4.250 -0.1563 0.03752 0.03353 -0.0671 0.9810 0.0569
-4.000 -0.1154 0.02610 0.02120 -0.0740 0.9769 0.0508
-3.750 -0.0740 0.02082 0.01481 -0.0777 0.9732 0.0546
-3.500 -0.0358 0.01844 0.01196 -0.0800 0.9678 0.0575
-3.250 0.0048 0.01784 0.01127 -0.0825 0.9609 0.0632
-3.000 0.0462 0.01670 0.00973 -0.0848 0.9550 0.0675
-2.750 0.0849 0.01553 0.00853 -0.0869 0.9478 0.0752
-2.500 0.1276 0.01449 0.00740 -0.0896 0.9424 0.0875
-2.250 0.1674 0.01391 0.00677 -0.0916 0.9340 0.1082
-2.000 0.2123 0.01388 0.00674 -0.0947 0.9277 0.1241
-1.750 0.2531 0.01366 0.00642 -0.0968 0.9185 0.1355
-1.500 0.2914 0.01332 0.00608 -0.0986 0.9071 0.1436
-1.250 0.3291 0.01289 0.00559 -0.1001 0.8937 0.1516
-1.000 0.3638 0.01263 0.00526 -0.1010 0.8766 0.1609
-0.750 0.3953 0.01220 0.00485 -0.1013 0.8557 0.1693
-0.500 0.4240 0.01183 0.00442 -0.1010 0.8301 0.1792
-0.250 0.4520 0.01151 0.00404 -0.1006 0.8020 0.1925
0.000 0.4802 0.01129 0.00375 -0.1002 0.7743 0.2076
0.250 0.5076 0.01124 0.00356 -0.0997 0.7476 0.2216
0.500 0.5338 0.01132 0.00348 -0.0990 0.7223 0.2344
0.750 0.5594 0.01141 0.00346 -0.0982 0.7000 0.2462
1.000 0.5845 0.01148 0.00348 -0.0975 0.6807 0.2580
1.250 0.6099 0.01155 0.00353 -0.0969 0.6647 0.2727
1.500 0.6353 0.01159 0.00357 -0.0962 0.6502 0.2911
1.750 0.6604 0.01155 0.00361 -0.0956 0.6367 0.3204
2.000 0.7000 0.01024 0.00365 -0.0980 0.6225 1.0000
2.250 0.7254 0.01045 0.00374 -0.0973 0.6099 1.0000
2.500 0.7506 0.01066 0.00383 -0.0966 0.5968 1.0000
2.750 0.7756 0.01085 0.00394 -0.0958 0.5832 1.0000
3.000 0.8003 0.01104 0.00406 -0.0950 0.5690 1.0000
3.250 0.8250 0.01124 0.00421 -0.0942 0.5549 1.0000
3.500 0.8497 0.01144 0.00437 -0.0935 0.5415 1.0000
3.750 0.8745 0.01164 0.00454 -0.0927 0.5286 1.0000
4.000 0.8991 0.01185 0.00472 -0.0919 0.5150 1.0000
4.250 0.9237 0.01207 0.00494 -0.0912 0.5019 1.0000
4.500 0.9483 0.01230 0.00516 -0.0904 0.4892 1.0000
4.750 0.9725 0.01252 0.00537 -0.0896 0.4751 1.0000
5.000 0.9964 0.01274 0.00560 -0.0887 0.4600 1.0000
5.250 1.0193 0.01293 0.00581 -0.0876 0.4404 1.0000
5.500 1.0414 0.01314 0.00598 -0.0864 0.4167 1.0000
5.750 1.0630 0.01340 0.00617 -0.0851 0.3903 1.0000
6.000 1.0844 0.01370 0.00642 -0.0839 0.3622 1.0000
6.250 1.1058 0.01406 0.00674 -0.0827 0.3340 1.0000
6.500 1.1260 0.01453 0.00709 -0.0813 0.2976 1.0000
6.750 1.1441 0.01521 0.00755 -0.0798 0.2544 1.0000
7.000 1.1623 0.01596 0.00810 -0.0782 0.2134 1.0000
7.250 1.1761 0.01717 0.00883 -0.0762 0.1357 1.0000
7.500 1.1881 0.01863 0.00990 -0.0739 0.0827 1.0000
7.750 1.1996 0.02012 0.01103 -0.0714 0.0375 1.0000
8.000 1.2153 0.02116 0.01213 -0.0693 0.0324 1.0000
8.250 1.2318 0.02206 0.01322 -0.0674 0.0307 1.0000
8.500 1.2458 0.02310 0.01442 -0.0652 0.0290 1.0000
8.750 1.2563 0.02433 0.01579 -0.0626 0.0272 1.0000
9.000 1.2626 0.02574 0.01734 -0.0594 0.0259 1.0000
9.250 1.2651 0.02721 0.01892 -0.0557 0.0252 1.0000
9.500 1.2658 0.02891 0.02070 -0.0520 0.0247 1.0000
9.750 1.2673 0.03084 0.02271 -0.0486 0.0243 1.0000
10.000 1.2731 0.03293 0.02484 -0.0460 0.0240 1.0000
10.250 1.2848 0.03470 0.02669 -0.0441 0.0239 1.0000
10.500 1.3008 0.03670 0.02877 -0.0426 0.0238 1.0000
10.750 1.3182 0.03873 0.03093 -0.0414 0.0237 1.0000
11.000 1.3310 0.04061 0.03298 -0.0398 0.0234 1.0000
11.250 1.3375 0.04230 0.03490 -0.0377 0.0226 1.0000
11.500 1.3490 0.04481 0.03762 -0.0362 0.0226 1.0000
11.750 1.3593 0.04785 0.04090 -0.0348 0.0229 1.0000
12.000 1.3654 0.05146 0.04478 -0.0332 0.0233 1.0000
12.250 1.3874 0.05585 0.04937 -0.0331 0.0244 1.0000
12.500 1.3831 0.05724 0.05097 -0.0305 0.0249 1.0000
12.750 1.3714 0.05932 0.05339 -0.0280 0.0258 1.0000
13.000 1.3471 0.06387 0.05846 -0.0264 0.0276 1.0000
13.250 1.3266 0.06928 0.06424 -0.0262 0.0290 1.0000
13.500 1.3082 0.07486 0.07008 -0.0270 0.0300 1.0000
13.750 1.2889 0.08086 0.07631 -0.0285 0.0308 1.0000
14.000 1.2684 0.08771 0.08335 -0.0307 0.0316 1.0000
14.750 1.0680 0.10576 0.10221 -0.0397 0.0275 1.0000
15.000 1.0388 0.11349 0.11015 -0.0451 0.0276 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 144 (MVA H.21) AIRFOIL (goe144-il)