GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.01 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe222-il-1000000-n5.txt Download as CSV file: xf-goe222-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -0.5248 0.12101 0.11855 -0.1003 0.9683 0.0175
-19.250 -0.5437 0.11402 0.11145 -0.1042 0.9656 0.0178
-19.000 -0.5581 0.10798 0.10531 -0.1076 0.9624 0.0181
-18.750 -0.5684 0.10275 0.09998 -0.1105 0.9591 0.0183
-18.500 -0.5757 0.09812 0.09526 -0.1130 0.9561 0.0185
-18.250 -0.5826 0.09348 0.09054 -0.1157 0.9532 0.0187
-18.000 -0.5876 0.08928 0.08626 -0.1181 0.9495 0.0188
-17.750 -0.5924 0.08521 0.08214 -0.1204 0.9456 0.0191
-17.500 -0.5973 0.08116 0.07801 -0.1227 0.9419 0.0192
-17.250 -0.5985 0.07760 0.07440 -0.1249 0.9385 0.0194
-17.000 -0.6005 0.07391 0.07067 -0.1272 0.9343 0.0196
-16.750 -0.6002 0.07065 0.06735 -0.1291 0.9298 0.0198
-16.500 -0.6007 0.06734 0.06397 -0.1311 0.9257 0.0200
-16.250 -0.5986 0.06428 0.06086 -0.1330 0.9219 0.0202
-16.000 -0.5967 0.06123 0.05775 -0.1350 0.9172 0.0204
-15.750 -0.5936 0.05841 0.05486 -0.1368 0.9119 0.0206
-15.500 -0.5908 0.05557 0.05194 -0.1387 0.9068 0.0209
-15.250 -0.5864 0.05290 0.04922 -0.1405 0.9007 0.0211
-15.000 -0.5828 0.05022 0.04645 -0.1423 0.8936 0.0213
-14.750 -0.5776 0.04772 0.04389 -0.1440 0.8862 0.0216
-14.500 -0.5735 0.04518 0.04125 -0.1458 0.8768 0.0218
-14.250 -0.5686 0.04277 0.03875 -0.1476 0.8661 0.0219
-14.000 -0.5644 0.04036 0.03623 -0.1494 0.8530 0.0221
-13.750 -0.5598 0.03800 0.03375 -0.1512 0.8361 0.0222
-13.500 -0.5553 0.03569 0.03129 -0.1530 0.8142 0.0223
-13.250 -0.5563 0.03304 0.02850 -0.1550 0.7904 0.0226
-13.000 -0.5482 0.03040 0.02572 -0.1587 0.7726 0.0228
-12.750 -0.5334 0.02793 0.02314 -0.1629 0.7604 0.0231
-12.500 -0.5132 0.02562 0.02075 -0.1673 0.7523 0.0234
-12.000 -0.4630 0.02162 0.01656 -0.1760 0.7402 0.0240
-11.750 -0.4342 0.01999 0.01483 -0.1799 0.7359 0.0243
-11.500 -0.4049 0.01876 0.01350 -0.1829 0.7318 0.0248
-11.250 -0.3768 0.01795 0.01261 -0.1847 0.7281 0.0251
-11.000 -0.3488 0.01726 0.01183 -0.1862 0.7247 0.0254
-10.750 -0.3202 0.01664 0.01114 -0.1875 0.7224 0.0257
-10.500 -0.2915 0.01614 0.01058 -0.1886 0.7201 0.0260
-10.250 -0.2628 0.01560 0.00999 -0.1897 0.7177 0.0263
-10.000 -0.2343 0.01493 0.00926 -0.1910 0.7148 0.0267
-9.750 -0.2057 0.01445 0.00872 -0.1919 0.7113 0.0271
-9.250 -0.1479 0.01371 0.00787 -0.1935 0.7050 0.0279
-9.000 -0.1184 0.01338 0.00751 -0.1943 0.7029 0.0284
-8.750 -0.0889 0.01306 0.00716 -0.1950 0.7004 0.0288
-8.500 -0.0594 0.01275 0.00681 -0.1957 0.6979 0.0292
-8.250 -0.0299 0.01247 0.00648 -0.1964 0.6954 0.0296
-8.000 -0.0004 0.01222 0.00617 -0.1970 0.6930 0.0299
-7.750 0.0290 0.01199 0.00589 -0.1976 0.6905 0.0303
-7.500 0.0584 0.01178 0.00563 -0.1982 0.6879 0.0305
-7.250 0.0886 0.01144 0.00527 -0.1990 0.6859 0.0312
-7.000 0.1187 0.01119 0.00500 -0.1997 0.6834 0.0319
-6.750 0.1485 0.01099 0.00478 -0.2003 0.6806 0.0326
-6.500 0.1784 0.01081 0.00457 -0.2008 0.6780 0.0333
-6.250 0.2080 0.01065 0.00437 -0.2014 0.6753 0.0340
-6.000 0.2375 0.01051 0.00419 -0.2018 0.6724 0.0346
-5.750 0.2670 0.01039 0.00403 -0.2023 0.6695 0.0352
-5.500 0.2973 0.01021 0.00384 -0.2029 0.6675 0.0362
-5.250 0.3274 0.01005 0.00368 -0.2035 0.6652 0.0375
-5.000 0.3574 0.00992 0.00354 -0.2040 0.6628 0.0389
-4.750 0.3872 0.00981 0.00342 -0.2045 0.6599 0.0404
-4.500 0.4167 0.00970 0.00329 -0.2050 0.6567 0.0429
-4.250 0.4460 0.00960 0.00317 -0.2053 0.6536 0.0463
-4.000 0.4758 0.00949 0.00305 -0.2058 0.6510 0.0514
-3.750 0.5066 0.00915 0.00285 -0.2068 0.6483 0.0911
-3.500 0.5367 0.00895 0.00273 -0.2074 0.6449 0.1173
-3.250 0.5666 0.00875 0.00260 -0.2081 0.6410 0.1472
-3.000 0.5962 0.00847 0.00247 -0.2088 0.6368 0.2001
-2.750 0.6257 0.00835 0.00244 -0.2093 0.6329 0.2327
-2.500 0.6552 0.00830 0.00243 -0.2097 0.6278 0.2519
-2.250 0.6837 0.00829 0.00244 -0.2099 0.6213 0.2655
-2.000 0.7120 0.00832 0.00244 -0.2101 0.6146 0.2745
-1.750 0.7393 0.00837 0.00246 -0.2100 0.6027 0.2824
-1.500 0.7648 0.00849 0.00251 -0.2096 0.5831 0.2910
-1.000 0.8094 0.00905 0.00279 -0.2075 0.5257 0.3051
-0.750 0.8330 0.00929 0.00292 -0.2068 0.5070 0.3089
-0.500 0.8574 0.00950 0.00305 -0.2062 0.4925 0.3122
-0.250 0.8818 0.00969 0.00318 -0.2057 0.4798 0.3155
0.000 0.9056 0.00991 0.00333 -0.2050 0.4671 0.3185
0.250 0.9304 0.01007 0.00345 -0.2045 0.4569 0.3217
0.500 0.9545 0.01026 0.00358 -0.2038 0.4488 0.3253
0.750 0.9793 0.01038 0.00368 -0.2033 0.4435 0.3285
1.000 1.0027 0.01050 0.00380 -0.2025 0.4381 0.3328
1.250 1.0247 0.01066 0.00394 -0.2015 0.4329 0.3361
1.500 1.0484 0.01078 0.00407 -0.2008 0.4292 0.3392
1.750 1.0729 0.01092 0.00420 -0.2002 0.4254 0.3422
2.000 1.0974 0.01108 0.00435 -0.1997 0.4216 0.3447
2.250 1.1212 0.01128 0.00453 -0.1991 0.4173 0.3473
2.500 1.1451 0.01148 0.00472 -0.1985 0.4126 0.3508
2.750 1.1698 0.01164 0.00490 -0.1981 0.4083 0.3545
3.000 1.1937 0.01184 0.00510 -0.1975 0.4041 0.3584
3.250 1.2170 0.01206 0.00531 -0.1968 0.4006 0.3619
3.500 1.2400 0.01229 0.00553 -0.1961 0.3974 0.3646
3.750 1.2641 0.01247 0.00574 -0.1957 0.3950 0.3685
4.000 1.2883 0.01265 0.00595 -0.1952 0.3927 0.3724
4.250 1.3119 0.01286 0.00618 -0.1946 0.3896 0.3762
4.500 1.3347 0.01310 0.00643 -0.1939 0.3861 0.3798
4.750 1.3569 0.01336 0.00670 -0.1932 0.3829 0.3833
5.000 1.3782 0.01367 0.00702 -0.1923 0.3793 0.3882
5.250 1.4012 0.01390 0.00729 -0.1917 0.3764 0.3932
5.500 1.4239 0.01416 0.00757 -0.1910 0.3728 0.3974
6.000 1.4664 0.01480 0.00824 -0.1893 0.3649 0.4063
6.250 1.4866 0.01517 0.00863 -0.1883 0.3614 0.4116
6.500 1.5087 0.01545 0.00896 -0.1876 0.3579 0.4174
6.750 1.5297 0.01580 0.00933 -0.1868 0.3527 0.4243
7.000 1.5471 0.01632 0.00984 -0.1854 0.3459 0.4317
7.500 1.5838 0.01730 0.01085 -0.1830 0.3304 0.4475
7.750 1.5981 0.01801 0.01152 -0.1813 0.3161 0.4564
8.000 1.6065 0.01906 0.01248 -0.1787 0.2929 0.4672
8.250 1.6086 0.02050 0.01379 -0.1754 0.2661 0.4788
8.500 1.6136 0.02184 0.01506 -0.1725 0.2461 0.4936
8.750 1.6204 0.02310 0.01628 -0.1700 0.2310 0.5105
9.000 1.6281 0.02436 0.01752 -0.1678 0.2194 0.5264
9.250 1.6413 0.02530 0.01849 -0.1663 0.2130 0.5418
9.500 1.6520 0.02645 0.01964 -0.1645 0.2063 0.5558
9.750 1.6653 0.02744 0.02067 -0.1632 0.2012 0.5702
10.000 1.6789 0.02843 0.02170 -0.1619 0.1970 0.5856
10.250 1.6914 0.02951 0.02283 -0.1605 0.1928 0.6028
10.500 1.7029 0.03072 0.02409 -0.1592 0.1884 0.6220
10.750 1.7180 0.03167 0.02514 -0.1583 0.1858 0.6522
11.000 1.7309 0.03227 0.02630 -0.1569 0.1826 1.0000
11.250 1.7426 0.03351 0.02754 -0.1557 0.1782 1.0000
11.500 1.7510 0.03504 0.02907 -0.1541 0.1731 1.0000
11.750 1.7628 0.03629 0.03034 -0.1530 0.1687 1.0000
12.000 1.7701 0.03796 0.03199 -0.1515 0.1613 1.0000
12.250 1.7774 0.03964 0.03367 -0.1500 0.1544 1.0000
12.500 1.7804 0.04172 0.03571 -0.1482 0.1440 1.0000
12.750 1.7782 0.04429 0.03822 -0.1462 0.1308 1.0000
13.000 1.7742 0.04708 0.04095 -0.1441 0.1182 1.0000
13.250 1.7692 0.05002 0.04385 -0.1420 0.1060 1.0000
13.500 1.7595 0.05348 0.04726 -0.1398 0.0910 1.0000
13.750 1.7321 0.05879 0.05243 -0.1366 0.0620 1.0000
14.000 1.7198 0.06278 0.05640 -0.1347 0.0505 1.0000
14.250 1.7164 0.06593 0.05959 -0.1334 0.0459 1.0000
14.500 1.7171 0.06863 0.06233 -0.1323 0.0424 1.0000
14.750 1.7140 0.07182 0.06556 -0.1312 0.0383 1.0000
15.000 1.7113 0.07503 0.06880 -0.1303 0.0337 1.0000
15.250 1.7041 0.07882 0.07260 -0.1293 0.0259 1.0000
15.500 1.6915 0.08333 0.07710 -0.1283 0.0173 1.0000
15.750 1.6877 0.08682 0.08063 -0.1276 0.0151 1.0000
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