GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 200,000 Max Cl/Cd: 73.25 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe122-il-200000.txt Download as CSV file: xf-goe122-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4284 0.10345 0.10004 -0.0019 1.0000 0.0292
-8.250 -0.4255 0.10079 0.09742 -0.0065 1.0000 0.0296
-8.000 -0.4215 0.09779 0.09447 -0.0116 1.0000 0.0298
-7.750 -0.4102 0.09396 0.09066 -0.0184 1.0000 0.0300
-7.500 -0.4037 0.08855 0.08528 -0.0203 1.0000 0.0303
-7.250 -0.3979 0.08497 0.08173 -0.0154 1.0000 0.0313
-7.000 -0.3874 0.08163 0.07841 -0.0165 1.0000 0.0321
-6.750 -0.3752 0.07806 0.07485 -0.0195 1.0000 0.0330
-6.500 -0.3613 0.07434 0.07113 -0.0232 1.0000 0.0341
-6.250 -0.3454 0.07049 0.06726 -0.0274 1.0000 0.0354
-6.000 -0.3238 0.06638 0.06310 -0.0336 1.0000 0.0374
-5.750 -0.2904 0.06247 0.05891 -0.0430 1.0000 0.0387
-5.500 -0.2874 0.05723 0.05372 -0.0427 1.0000 0.0395
-5.250 -0.2855 0.05475 0.05131 -0.0403 1.0000 0.0403
-5.000 -0.2813 0.05272 0.04931 -0.0383 1.0000 0.0414
-4.750 -0.2647 0.05016 0.04671 -0.0392 0.9984 0.0439
-4.500 -0.2074 0.04392 0.03991 -0.0495 0.9924 0.0509
-4.250 -0.1761 0.04068 0.03673 -0.0527 0.9866 0.0536
-4.000 -0.1255 0.03701 0.03242 -0.0588 0.9806 0.0635
-3.750 -0.0927 0.03358 0.02915 -0.0620 0.9744 0.0673
-3.500 -0.0508 0.03063 0.02587 -0.0661 0.9681 0.0796
-3.250 -0.0124 0.02838 0.02326 -0.0689 0.9590 0.0928
-3.000 0.0223 0.02643 0.02110 -0.0709 0.9486 0.1071
-2.750 0.0537 0.02443 0.01901 -0.0723 0.9373 0.1227
-2.500 0.0809 0.02289 0.01748 -0.0726 0.9242 0.1415
-2.250 0.1056 0.02172 0.01620 -0.0721 0.9094 0.1692
-1.500 0.1986 0.01601 0.00877 -0.0674 0.8652 0.0716
-1.250 0.2251 0.01491 0.00737 -0.0661 0.8490 0.0662
-1.000 0.2512 0.01426 0.00655 -0.0649 0.8321 0.0642
-0.750 0.2771 0.01365 0.00584 -0.0639 0.8146 0.0638
-0.500 0.3026 0.01297 0.00512 -0.0630 0.7968 0.0649
-0.250 0.3283 0.01249 0.00462 -0.0621 0.7783 0.0677
0.000 0.3545 0.01210 0.00418 -0.0614 0.7583 0.0687
0.250 0.3807 0.01180 0.00381 -0.0607 0.7381 0.0703
0.500 0.4071 0.01161 0.00351 -0.0600 0.7157 0.0731
0.750 0.4334 0.01151 0.00324 -0.0593 0.6922 0.0777
1.000 0.4600 0.01139 0.00304 -0.0587 0.6674 0.0923
1.250 0.4869 0.00921 0.00297 -0.0584 0.6451 1.0000
1.500 0.5136 0.00941 0.00294 -0.0579 0.6222 1.0000
1.750 0.5401 0.00964 0.00295 -0.0575 0.6011 1.0000
2.000 0.5669 0.00984 0.00299 -0.0571 0.5791 1.0000
2.250 0.5935 0.01006 0.00305 -0.0568 0.5594 1.0000
2.500 0.6203 0.01028 0.00314 -0.0565 0.5418 1.0000
2.750 0.6472 0.01050 0.00326 -0.0563 0.5261 1.0000
3.000 0.6741 0.01073 0.00339 -0.0560 0.5116 1.0000
3.250 0.7009 0.01096 0.00354 -0.0558 0.4981 1.0000
3.500 0.7278 0.01121 0.00373 -0.0556 0.4858 1.0000
3.750 0.7544 0.01145 0.00391 -0.0554 0.4718 1.0000
4.000 0.7809 0.01170 0.00410 -0.0551 0.4575 1.0000
4.250 0.8074 0.01195 0.00433 -0.0549 0.4437 1.0000
4.500 0.8339 0.01220 0.00457 -0.0546 0.4305 1.0000
4.750 0.8602 0.01245 0.00481 -0.0544 0.4167 1.0000
5.000 0.8865 0.01271 0.00507 -0.0541 0.4038 1.0000
5.250 0.9126 0.01295 0.00534 -0.0539 0.3894 1.0000
5.500 0.9387 0.01317 0.00560 -0.0536 0.3741 1.0000
5.750 0.9646 0.01340 0.00586 -0.0533 0.3577 1.0000
6.000 0.9902 0.01364 0.00612 -0.0530 0.3388 1.0000
6.250 1.0160 0.01387 0.00642 -0.0527 0.3160 1.0000
6.500 1.0406 0.01421 0.00669 -0.0523 0.2794 1.0000
6.750 1.0635 0.01485 0.00710 -0.0517 0.2194 1.0000
7.000 1.0824 0.01619 0.00799 -0.0509 0.1515 1.0000
7.500 1.1190 0.01914 0.01040 -0.0489 0.0588 1.0000
7.750 1.1385 0.02031 0.01167 -0.0479 0.0532 1.0000
8.000 1.1575 0.02145 0.01295 -0.0468 0.0495 1.0000
8.250 1.1727 0.02298 0.01454 -0.0453 0.0462 1.0000
8.500 1.1849 0.02488 0.01651 -0.0435 0.0433 1.0000
8.750 1.2021 0.02617 0.01791 -0.0421 0.0412 1.0000
9.000 1.2184 0.02773 0.01954 -0.0406 0.0393 1.0000
9.250 1.2347 0.02940 0.02126 -0.0393 0.0372 1.0000
9.500 1.2511 0.03181 0.02362 -0.0381 0.0347 1.0000
9.750 1.2710 0.03518 0.02714 -0.0372 0.0332 1.0000
10.000 1.2887 0.03689 0.02910 -0.0359 0.0324 1.0000
10.250 1.3054 0.03909 0.03154 -0.0346 0.0317 1.0000
10.500 1.3191 0.04125 0.03398 -0.0331 0.0307 1.0000
10.750 1.3301 0.04345 0.03644 -0.0315 0.0294 1.0000
11.000 1.3387 0.04615 0.03940 -0.0297 0.0287 1.0000
11.250 1.3425 0.04931 0.04291 -0.0277 0.0287 1.0000
11.500 1.3399 0.05269 0.04664 -0.0252 0.0289 1.0000
11.750 1.3302 0.05612 0.05038 -0.0224 0.0293 1.0000
12.000 1.3173 0.05991 0.05446 -0.0202 0.0299 1.0000
12.250 1.3019 0.06409 0.05890 -0.0189 0.0305 1.0000
12.500 1.2846 0.06872 0.06378 -0.0185 0.0311 1.0000
12.750 1.2659 0.07391 0.06918 -0.0190 0.0316 1.0000
13.000 1.2458 0.07992 0.07538 -0.0204 0.0323 1.0000
13.250 1.1022 0.07671 0.07236 -0.0103 0.0310 1.0000
13.500 1.0758 0.08299 0.07881 -0.0121 0.0313 1.0000
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Polar data table (+)
Polar graphs
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