GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 500,000 Max Cl/Cd: 84.81 at α=0.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe222-il-500000-n5.txt Download as CSV file: xf-goe222-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 222 (MVA H.33) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.4238 0.09710 0.09385 -0.1189 0.9672 0.0224
-16.750 -0.4357 0.09129 0.08795 -0.1223 0.9631 0.0226
-16.500 -0.4436 0.08611 0.08269 -0.1255 0.9594 0.0228
-16.250 -0.4491 0.08140 0.07790 -0.1286 0.9562 0.0230
-16.000 -0.4544 0.07704 0.07347 -0.1313 0.9520 0.0232
-15.750 -0.4587 0.07288 0.06923 -0.1339 0.9476 0.0234
-15.500 -0.4623 0.06886 0.06512 -0.1364 0.9433 0.0236
-15.250 -0.4644 0.06514 0.06132 -0.1388 0.9392 0.0239
-15.000 -0.4659 0.06159 0.05768 -0.1412 0.9340 0.0241
-14.750 -0.4674 0.05812 0.05411 -0.1434 0.9286 0.0244
-14.500 -0.4679 0.05484 0.05073 -0.1456 0.9235 0.0247
-14.250 -0.4674 0.05178 0.04757 -0.1477 0.9171 0.0250
-14.000 -0.4668 0.04884 0.04451 -0.1497 0.9105 0.0253
-13.750 -0.4654 0.04609 0.04165 -0.1516 0.9036 0.0256
-13.500 -0.4625 0.04356 0.03900 -0.1533 0.8954 0.0258
-13.250 -0.4583 0.04113 0.03645 -0.1550 0.8870 0.0260
-13.000 -0.4528 0.03890 0.03411 -0.1565 0.8773 0.0263
-12.750 -0.4450 0.03700 0.03217 -0.1577 0.8666 0.0266
-12.500 -0.4364 0.03509 0.03018 -0.1591 0.8546 0.0268
-12.250 -0.4275 0.03324 0.02824 -0.1605 0.8407 0.0271
-12.000 -0.4180 0.03146 0.02635 -0.1622 0.8256 0.0274
-11.750 -0.4028 0.02965 0.02442 -0.1648 0.8113 0.0277
-11.500 -0.3844 0.02789 0.02254 -0.1678 0.7985 0.0280
-11.250 -0.3632 0.02620 0.02072 -0.1710 0.7880 0.0284
-11.000 -0.3393 0.02461 0.01899 -0.1744 0.7790 0.0289
-10.750 -0.3131 0.02314 0.01739 -0.1778 0.7718 0.0294
-10.500 -0.2859 0.02189 0.01599 -0.1806 0.7655 0.0299
-10.250 -0.2592 0.02095 0.01490 -0.1826 0.7603 0.0302
-10.000 -0.2324 0.02012 0.01398 -0.1842 0.7559 0.0306
-9.750 -0.2061 0.01920 0.01301 -0.1857 0.7517 0.0310
-9.500 -0.1788 0.01849 0.01224 -0.1870 0.7479 0.0315
-9.250 -0.1509 0.01791 0.01158 -0.1882 0.7443 0.0321
-9.000 -0.1227 0.01736 0.01098 -0.1893 0.7410 0.0326
-8.750 -0.0943 0.01684 0.01039 -0.1903 0.7374 0.0331
-8.500 -0.0658 0.01635 0.00983 -0.1912 0.7335 0.0337
-8.250 -0.0372 0.01590 0.00930 -0.1921 0.7296 0.0342
-8.000 -0.0084 0.01550 0.00881 -0.1929 0.7262 0.0347
-7.750 0.0209 0.01512 0.00836 -0.1937 0.7234 0.0352
-7.500 0.0503 0.01465 0.00785 -0.1947 0.7206 0.0359
-7.250 0.0797 0.01422 0.00739 -0.1956 0.7173 0.0367
-7.000 0.1090 0.01389 0.00701 -0.1964 0.7138 0.0375
-6.750 0.1385 0.01361 0.00666 -0.1971 0.7106 0.0383
-6.500 0.1682 0.01335 0.00633 -0.1978 0.7077 0.0392
-6.250 0.1979 0.01311 0.00603 -0.1985 0.7052 0.0400
-6.000 0.2276 0.01287 0.00576 -0.1991 0.7023 0.0409
-5.750 0.2573 0.01257 0.00544 -0.1998 0.6989 0.0422
-5.500 0.2868 0.01235 0.00517 -0.2004 0.6952 0.0438
-5.250 0.3163 0.01219 0.00495 -0.2009 0.6917 0.0457
-5.000 0.3459 0.01205 0.00475 -0.2014 0.6887 0.0480
-4.750 0.3759 0.01184 0.00452 -0.2021 0.6865 0.0516
-4.500 0.4058 0.01164 0.00432 -0.2027 0.6841 0.0575
-4.250 0.4364 0.01117 0.00403 -0.2038 0.6815 0.1053
-4.000 0.4666 0.01081 0.00379 -0.2047 0.6787 0.1458
-3.750 0.4968 0.01045 0.00362 -0.2056 0.6758 0.2066
-3.500 0.5263 0.01034 0.00358 -0.2061 0.6727 0.2408
-3.250 0.5555 0.01034 0.00356 -0.2065 0.6697 0.2583
-3.000 0.5846 0.01030 0.00356 -0.2068 0.6664 0.2699
-2.750 0.6135 0.01029 0.00356 -0.2070 0.6625 0.2793
-2.500 0.6422 0.01030 0.00357 -0.2073 0.6587 0.2894
-2.250 0.6707 0.01032 0.00357 -0.2074 0.6549 0.2971
-2.000 0.6991 0.01037 0.00361 -0.2076 0.6512 0.3075
-1.750 0.7276 0.01038 0.00364 -0.2077 0.6468 0.3154
-1.500 0.7556 0.01040 0.00367 -0.2078 0.6416 0.3203
-1.250 0.7830 0.01045 0.00367 -0.2078 0.6362 0.3247
-1.000 0.8108 0.01049 0.00367 -0.2078 0.6305 0.3282
-0.750 0.8380 0.01050 0.00370 -0.2077 0.6230 0.3317
-0.500 0.8643 0.01055 0.00373 -0.2074 0.6141 0.3356
-0.250 0.8889 0.01064 0.00376 -0.2068 0.6008 0.3394
0.000 0.9119 0.01077 0.00381 -0.2059 0.5823 0.3427
0.250 0.9321 0.01099 0.00389 -0.2045 0.5596 0.3456
0.500 0.9513 0.01126 0.00404 -0.2029 0.5390 0.3486
0.750 0.9709 0.01154 0.00423 -0.2014 0.5219 0.3516
1.000 0.9892 0.01182 0.00443 -0.1996 0.5065 0.3545
1.250 1.0072 0.01209 0.00463 -0.1978 0.4933 0.3576
1.500 1.0258 0.01238 0.00485 -0.1961 0.4822 0.3606
1.750 1.0472 0.01264 0.00506 -0.1951 0.4731 0.3635
2.000 1.0691 0.01291 0.00530 -0.1941 0.4662 0.3667
2.250 1.0928 0.01312 0.00552 -0.1935 0.4601 0.3706
2.500 1.1151 0.01338 0.00577 -0.1927 0.4543 0.3746
2.750 1.1369 0.01367 0.00604 -0.1918 0.4493 0.3784
3.000 1.1605 0.01389 0.00626 -0.1912 0.4447 0.3817
3.250 1.1829 0.01416 0.00653 -0.1904 0.4393 0.3852
3.500 1.2036 0.01449 0.00685 -0.1894 0.4339 0.3891
3.750 1.2258 0.01476 0.00714 -0.1886 0.4298 0.3933
4.000 1.2487 0.01502 0.00741 -0.1879 0.4259 0.3979
4.250 1.2706 0.01531 0.00772 -0.1871 0.4218 0.4023
4.500 1.2914 0.01565 0.00808 -0.1862 0.4177 0.4072
4.750 1.3113 0.01603 0.00846 -0.1851 0.4137 0.4121
5.000 1.3342 0.01629 0.00877 -0.1845 0.4104 0.4171
5.250 1.3561 0.01660 0.00912 -0.1837 0.4071 0.4221
5.500 1.3770 0.01695 0.00951 -0.1828 0.4035 0.4282
5.750 1.3965 0.01737 0.00994 -0.1818 0.3993 0.4350
6.000 1.4157 0.01781 0.01041 -0.1807 0.3955 0.4422
6.250 1.4374 0.01813 0.01081 -0.1800 0.3923 0.4510
6.500 1.4582 0.01851 0.01124 -0.1791 0.3888 0.4595
6.750 1.4782 0.01892 0.01172 -0.1782 0.3853 0.4699
7.000 1.4969 0.01942 0.01225 -0.1771 0.3817 0.4811
7.500 1.5356 0.02034 0.01332 -0.1752 0.3747 0.5124
7.750 1.5549 0.02082 0.01388 -0.1743 0.3702 0.5299
8.000 1.5715 0.02144 0.01455 -0.1730 0.3652 0.5467
8.250 1.5881 0.02208 0.01524 -0.1718 0.3607 0.5626
8.500 1.6073 0.02259 0.01585 -0.1709 0.3559 0.5792
8.750 1.6231 0.02329 0.01661 -0.1696 0.3497 0.5968
9.000 1.6375 0.02409 0.01746 -0.1682 0.3416 0.6173
9.250 1.6483 0.02513 0.01854 -0.1664 0.3298 0.6429
9.500 1.6583 0.02626 0.01982 -0.1647 0.3123 0.7176
9.750 1.6544 0.02764 0.02139 -0.1607 0.2880 1.0000
10.000 1.6505 0.02990 0.02350 -0.1576 0.2632 1.0000
10.250 1.6509 0.03195 0.02546 -0.1550 0.2463 1.0000
10.500 1.6538 0.03388 0.02733 -0.1529 0.2344 1.0000
10.750 1.6606 0.03553 0.02897 -0.1512 0.2262 1.0000
11.000 1.6660 0.03733 0.03076 -0.1494 0.2192 1.0000
11.250 1.6761 0.03878 0.03223 -0.1482 0.2141 1.0000
11.500 1.6840 0.04043 0.03390 -0.1468 0.2092 1.0000
11.750 1.6899 0.04228 0.03574 -0.1453 0.2043 1.0000
12.000 1.6998 0.04378 0.03730 -0.1441 0.2007 1.0000
12.250 1.7095 0.04532 0.03888 -0.1430 0.1969 1.0000
12.500 1.7164 0.04713 0.04072 -0.1417 0.1927 1.0000
12.750 1.7210 0.04918 0.04278 -0.1403 0.1885 1.0000
13.000 1.7301 0.05081 0.04447 -0.1393 0.1847 1.0000
13.250 1.7378 0.05261 0.04632 -0.1382 0.1801 1.0000
13.500 1.7424 0.05470 0.04843 -0.1370 0.1753 1.0000
13.750 1.7465 0.05688 0.05065 -0.1358 0.1708 1.0000
14.000 1.7522 0.05891 0.05271 -0.1348 0.1643 1.0000
14.250 1.7522 0.06158 0.05539 -0.1335 0.1575 1.0000
14.500 1.7535 0.06414 0.05797 -0.1324 0.1486 1.0000
14.750 1.7481 0.06747 0.06127 -0.1311 0.1371 1.0000
15.000 1.7384 0.07134 0.06510 -0.1297 0.1245 1.0000
15.250 1.7275 0.07545 0.06918 -0.1285 0.1128 1.0000
15.500 1.7151 0.07983 0.07355 -0.1274 0.1012 1.0000
15.750 1.6957 0.08513 0.07880 -0.1263 0.0834 1.0000
16.000 1.6678 0.09163 0.08520 -0.1254 0.0596 1.0000
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Polar data table (+)
Polar graphs
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