GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 421 AIRFOIL (goe421-il) Reynolds number: 500,000 Max Cl/Cd: 76.64 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe421-il-500000-n5.txt Download as CSV file: xf-goe421-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 421 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.3169 0.08129 0.07785 -0.1513 0.9374 0.0300
-16.000 -0.3408 0.07457 0.07098 -0.1552 0.9321 0.0304
-15.750 -0.3493 0.07023 0.06657 -0.1577 0.9274 0.0307
-15.500 -0.3543 0.06642 0.06272 -0.1600 0.9227 0.0311
-15.250 -0.3601 0.06261 0.05887 -0.1624 0.9164 0.0315
-15.000 -0.3692 0.05839 0.05457 -0.1651 0.9104 0.0319
-14.750 -0.3784 0.05438 0.05048 -0.1678 0.9034 0.0322
-14.500 -0.3896 0.05016 0.04617 -0.1706 0.8957 0.0326
-14.250 -0.4012 0.04587 0.04178 -0.1738 0.8873 0.0329
-14.000 -0.4135 0.04139 0.03716 -0.1772 0.8782 0.0332
-13.750 -0.4269 0.03664 0.03230 -0.1812 0.8676 0.0335
-13.500 -0.4446 0.03068 0.02614 -0.1880 0.8564 0.0337
-13.250 -0.4352 0.02602 0.02120 -0.1952 0.8481 0.0342
-13.000 -0.4201 0.02437 0.01937 -0.1967 0.8413 0.0347
-12.750 -0.4039 0.02308 0.01795 -0.1974 0.8341 0.0353
-12.500 -0.3853 0.02206 0.01684 -0.1978 0.8278 0.0359
-12.250 -0.3652 0.02127 0.01596 -0.1979 0.8214 0.0366
-12.000 -0.3436 0.02059 0.01518 -0.1980 0.8156 0.0373
-11.750 -0.3214 0.01997 0.01445 -0.1980 0.8104 0.0380
-11.500 -0.2992 0.01939 0.01377 -0.1978 0.8045 0.0388
-11.250 -0.2761 0.01886 0.01311 -0.1977 0.7988 0.0395
-11.000 -0.2531 0.01832 0.01247 -0.1976 0.7936 0.0401
-10.750 -0.2308 0.01776 0.01186 -0.1973 0.7880 0.0409
-10.500 -0.2070 0.01730 0.01134 -0.1971 0.7828 0.0416
-10.250 -0.1824 0.01690 0.01084 -0.1970 0.7782 0.0424
-10.000 -0.1581 0.01652 0.01040 -0.1968 0.7732 0.0433
-9.750 -0.1336 0.01616 0.00996 -0.1965 0.7678 0.0442
-9.500 -0.1084 0.01585 0.00953 -0.1963 0.7627 0.0450
-9.250 -0.0839 0.01547 0.00908 -0.1960 0.7580 0.0458
-9.000 -0.0595 0.01507 0.00865 -0.1958 0.7530 0.0468
-8.750 -0.0344 0.01476 0.00828 -0.1955 0.7482 0.0477
-8.500 -0.0085 0.01450 0.00794 -0.1954 0.7438 0.0489
-8.250 0.0171 0.01425 0.00763 -0.1951 0.7393 0.0501
-8.000 0.0427 0.01402 0.00733 -0.1949 0.7342 0.0512
-7.750 0.0680 0.01374 0.00699 -0.1946 0.7293 0.0524
-7.500 0.0938 0.01348 0.00668 -0.1944 0.7250 0.0538
-7.250 0.1196 0.01325 0.00642 -0.1942 0.7207 0.0553
-7.000 0.1456 0.01306 0.00618 -0.1939 0.7161 0.0569
-6.750 0.1718 0.01291 0.00595 -0.1937 0.7116 0.0584
-6.500 0.1978 0.01270 0.00569 -0.1935 0.7073 0.0606
-6.250 0.2237 0.01251 0.00549 -0.1933 0.7028 0.0628
-6.000 0.2499 0.01236 0.00530 -0.1930 0.6983 0.0652
-5.750 0.2762 0.01223 0.00511 -0.1928 0.6941 0.0676
-5.500 0.3025 0.01208 0.00493 -0.1926 0.6901 0.0709
-5.250 0.3284 0.01195 0.00479 -0.1923 0.6854 0.0747
-5.000 0.3538 0.01181 0.00463 -0.1920 0.6800 0.0797
-4.750 0.3794 0.01174 0.00450 -0.1916 0.6747 0.0852
-4.500 0.4048 0.01159 0.00436 -0.1912 0.6696 0.0925
-4.250 0.4299 0.01148 0.00425 -0.1908 0.6641 0.1013
-4.000 0.4549 0.01137 0.00413 -0.1903 0.6589 0.1130
-3.750 0.4803 0.01125 0.00406 -0.1900 0.6544 0.1317
-3.500 0.5055 0.01119 0.00409 -0.1896 0.6492 0.1572
-3.250 0.5301 0.01122 0.00411 -0.1890 0.6435 0.1709
-3.000 0.5540 0.01128 0.00410 -0.1882 0.6381 0.1784
-2.750 0.5771 0.01130 0.00412 -0.1873 0.6320 0.1842
-2.500 0.5992 0.01136 0.00413 -0.1862 0.6257 0.1895
-2.250 0.6221 0.01144 0.00413 -0.1852 0.6201 0.1931
-2.000 0.6465 0.01145 0.00415 -0.1846 0.6152 0.1967
-1.750 0.6708 0.01149 0.00418 -0.1840 0.6107 0.2005
-1.500 0.6947 0.01156 0.00422 -0.1834 0.6062 0.2039
-1.250 0.7193 0.01164 0.00427 -0.1828 0.6019 0.2078
-1.000 0.7440 0.01174 0.00434 -0.1823 0.5969 0.2119
-0.750 0.7682 0.01180 0.00440 -0.1818 0.5915 0.2165
-0.500 0.7921 0.01191 0.00448 -0.1811 0.5866 0.2195
-0.250 0.8173 0.01198 0.00456 -0.1808 0.5817 0.2227
0.000 0.8416 0.01209 0.00466 -0.1803 0.5764 0.2251
0.250 0.8648 0.01224 0.00476 -0.1796 0.5712 0.2269
0.500 0.8893 0.01235 0.00486 -0.1791 0.5662 0.2287
0.750 0.9131 0.01249 0.00497 -0.1785 0.5603 0.2300
1.000 0.9352 0.01265 0.00511 -0.1776 0.5542 0.2323
1.250 0.9587 0.01279 0.00526 -0.1770 0.5484 0.2348
1.500 0.9814 0.01295 0.00542 -0.1763 0.5415 0.2374
1.750 1.0022 0.01318 0.00562 -0.1753 0.5347 0.2401
2.000 1.0247 0.01337 0.00581 -0.1745 0.5270 0.2432
2.250 1.0437 0.01367 0.00608 -0.1732 0.5185 0.2463
2.500 1.0650 0.01392 0.00631 -0.1722 0.5091 0.2497
2.750 1.0830 0.01426 0.00664 -0.1708 0.4989 0.2553
3.000 1.1011 0.01463 0.00699 -0.1694 0.4874 0.2622
3.250 1.1189 0.01502 0.00736 -0.1680 0.4758 0.2709
3.500 1.1350 0.01549 0.00782 -0.1663 0.4641 0.2856
3.750 1.1506 0.01599 0.00833 -0.1646 0.4517 0.3082
4.000 1.1673 0.01648 0.00885 -0.1632 0.4395 0.3381
4.250 1.1821 0.01707 0.00944 -0.1614 0.4280 0.3627
4.500 1.1961 0.01772 0.01008 -0.1596 0.4165 0.3825
4.750 1.2121 0.01830 0.01067 -0.1581 0.4058 0.4007
5.250 1.2423 0.01961 0.01200 -0.1551 0.3873 0.4369
5.500 1.2573 0.02029 0.01272 -0.1536 0.3798 0.4623
5.750 1.2743 0.02087 0.01340 -0.1526 0.3727 0.5082
6.000 1.2837 0.02080 0.01425 -0.1499 0.3666 1.0000
6.250 1.3007 0.02147 0.01491 -0.1488 0.3615 1.0000
6.500 1.3170 0.02220 0.01561 -0.1476 0.3561 1.0000
6.750 1.3302 0.02312 0.01650 -0.1461 0.3504 1.0000
7.000 1.3458 0.02390 0.01727 -0.1449 0.3455 1.0000
7.250 1.3615 0.02471 0.01807 -0.1438 0.3406 1.0000
7.500 1.3760 0.02560 0.01894 -0.1425 0.3361 1.0000
7.750 1.3893 0.02659 0.01991 -0.1412 0.3320 1.0000
8.000 1.4052 0.02742 0.02075 -0.1402 0.3289 1.0000
8.250 1.4221 0.02818 0.02153 -0.1393 0.3260 1.0000
8.500 1.4380 0.02903 0.02239 -0.1383 0.3233 1.0000
8.750 1.4529 0.02994 0.02332 -0.1373 0.3207 1.0000
9.000 1.4674 0.03090 0.02428 -0.1363 0.3180 1.0000
9.250 1.4804 0.03197 0.02536 -0.1351 0.3153 1.0000
9.500 1.4938 0.03303 0.02643 -0.1340 0.3128 1.0000
9.750 1.5107 0.03384 0.02728 -0.1333 0.3110 1.0000
10.000 1.5266 0.03473 0.02821 -0.1325 0.3090 1.0000
10.250 1.5411 0.03573 0.02924 -0.1316 0.3064 1.0000
10.500 1.5541 0.03685 0.03038 -0.1305 0.3027 1.0000
10.750 1.5640 0.03823 0.03175 -0.1293 0.2987 1.0000
11.000 1.5751 0.03952 0.03305 -0.1281 0.2952 1.0000
11.250 1.5907 0.04048 0.03407 -0.1275 0.2926 1.0000
11.500 1.6037 0.04166 0.03529 -0.1266 0.2891 1.0000
11.750 1.6146 0.04302 0.03667 -0.1256 0.2848 1.0000
12.000 1.6230 0.04459 0.03824 -0.1244 0.2807 1.0000
12.250 1.6348 0.04588 0.03957 -0.1235 0.2776 1.0000
12.500 1.6482 0.04705 0.04080 -0.1228 0.2740 1.0000
12.750 1.6582 0.04854 0.04232 -0.1219 0.2693 1.0000
13.000 1.6644 0.05037 0.04416 -0.1207 0.2644 1.0000
13.250 1.6754 0.05179 0.04563 -0.1199 0.2592 1.0000
13.500 1.6815 0.05370 0.04755 -0.1188 0.2517 1.0000
13.750 1.6864 0.05570 0.04956 -0.1177 0.2429 1.0000
14.000 1.6821 0.05864 0.05245 -0.1161 0.2252 1.0000
14.250 1.6530 0.06410 0.05769 -0.1131 0.1850 1.0000
14.500 1.6277 0.06931 0.06276 -0.1105 0.1617 1.0000
14.750 1.6171 0.07309 0.06653 -0.1090 0.1510 1.0000
15.000 1.6121 0.07638 0.06983 -0.1078 0.1438 1.0000
15.250 1.6080 0.07959 0.07307 -0.1068 0.1375 1.0000
15.500 1.6057 0.08268 0.07621 -0.1060 0.1316 1.0000
15.750 1.5995 0.08622 0.07977 -0.1051 0.1258 1.0000
16.000 1.5982 0.08922 0.08282 -0.1045 0.1203 1.0000
16.250 1.5918 0.09289 0.08651 -0.1039 0.1141 1.0000
16.500 1.5873 0.09635 0.09001 -0.1034 0.1077 1.0000
16.750 1.5774 0.10056 0.09422 -0.1030 0.1002 1.0000
17.000 1.5660 0.10500 0.09867 -0.1026 0.0905 1.0000
17.250 1.5476 0.11039 0.10404 -0.1024 0.0777 1.0000
17.500 1.5183 0.11738 0.11095 -0.1025 0.0577 1.0000
17.750 1.4902 0.12440 0.11791 -0.1030 0.0386 1.0000
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