GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 500,000 Max Cl/Cd: 85.38 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe431-il-500000-n5.txt Download as CSV file: xf-goe431-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 431 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.1222 0.11372 0.11112 -0.0997 0.9453 0.0082
-12.500 -0.2379 0.07814 0.07522 -0.1198 0.9383 0.0085
-12.250 -0.2331 0.07125 0.06820 -0.1283 0.9303 0.0088
-12.000 -0.2252 0.06478 0.06157 -0.1371 0.9202 0.0088
-11.750 -0.2149 0.06027 0.05694 -0.1432 0.9073 0.0090
-11.500 -0.2088 0.05631 0.05285 -0.1477 0.8936 0.0091
-11.250 -0.2068 0.05292 0.04934 -0.1506 0.8807 0.0092
-11.000 -0.2076 0.04977 0.04609 -0.1527 0.8694 0.0093
-10.750 -0.2109 0.04693 0.04315 -0.1539 0.8593 0.0094
-10.500 -0.2190 0.04413 0.04028 -0.1548 0.8498 0.0095
-10.250 -0.2187 0.04096 0.03701 -0.1580 0.8430 0.0096
-10.000 -0.2140 0.03752 0.03347 -0.1623 0.8368 0.0096
-9.750 -0.2029 0.03370 0.02953 -0.1683 0.8317 0.0098
-9.500 -0.1845 0.02963 0.02531 -0.1755 0.8277 0.0100
-9.250 -0.1601 0.02513 0.02062 -0.1838 0.8239 0.0103
-9.000 -0.1299 0.02065 0.01589 -0.1918 0.8207 0.0107
-8.750 -0.0999 0.01848 0.01347 -0.1958 0.8181 0.0111
-8.500 -0.0709 0.01723 0.01204 -0.1979 0.8158 0.0114
-8.250 -0.0419 0.01589 0.01052 -0.2000 0.8136 0.0122
-8.000 -0.0140 0.01503 0.00956 -0.2011 0.8108 0.0129
-7.750 0.0140 0.01436 0.00877 -0.2018 0.8075 0.0139
-7.500 0.0421 0.01375 0.00803 -0.2024 0.8040 0.0147
-7.250 0.0706 0.01316 0.00729 -0.2030 0.8009 0.0156
-7.000 0.0992 0.01260 0.00660 -0.2036 0.7981 0.0172
-6.750 0.1272 0.01216 0.00609 -0.2039 0.7950 0.0191
-6.500 0.1554 0.01171 0.00559 -0.2042 0.7921 0.0226
-6.250 0.1837 0.01132 0.00516 -0.2045 0.7893 0.0285
-6.000 0.2121 0.01097 0.00476 -0.2048 0.7863 0.0369
-5.750 0.2406 0.01067 0.00440 -0.2050 0.7834 0.0458
-5.500 0.2687 0.01038 0.00406 -0.2052 0.7801 0.0556
-5.250 0.2967 0.01001 0.00369 -0.2054 0.7765 0.0718
-5.000 0.3248 0.00980 0.00363 -0.2055 0.7732 0.1209
-4.750 0.3531 0.00987 0.00367 -0.2054 0.7700 0.1309
-4.500 0.3816 0.00993 0.00366 -0.2054 0.7671 0.1372
-4.250 0.4096 0.00999 0.00370 -0.2053 0.7638 0.1418
-4.000 0.4375 0.00994 0.00362 -0.2052 0.7600 0.1440
-3.750 0.4654 0.00993 0.00353 -0.2050 0.7559 0.1463
-3.500 0.4934 0.00994 0.00346 -0.2049 0.7520 0.1482
-3.250 0.5212 0.00990 0.00336 -0.2048 0.7480 0.1489
-3.000 0.5489 0.00975 0.00321 -0.2047 0.7439 0.1507
-2.750 0.5765 0.00965 0.00309 -0.2046 0.7396 0.1527
-2.500 0.6042 0.00961 0.00301 -0.2044 0.7353 0.1547
-2.250 0.6317 0.00954 0.00293 -0.2043 0.7307 0.1556
-2.000 0.6591 0.00947 0.00285 -0.2041 0.7253 0.1564
-1.750 0.6863 0.00943 0.00275 -0.2038 0.7194 0.1571
-1.500 0.7133 0.00937 0.00269 -0.2035 0.7117 0.1580
-1.250 0.7398 0.00935 0.00262 -0.2031 0.7029 0.1588
-1.000 0.7659 0.00933 0.00256 -0.2027 0.6910 0.1597
-0.750 0.7909 0.00935 0.00251 -0.2020 0.6734 0.1606
-0.500 0.8068 0.00965 0.00250 -0.1993 0.6020 0.1614
-0.250 0.8080 0.01074 0.00296 -0.1941 0.4922 0.1620
0.000 0.8269 0.01112 0.00317 -0.1923 0.4601 0.1628
0.250 0.8479 0.01140 0.00332 -0.1910 0.4375 0.1637
0.500 0.8698 0.01163 0.00346 -0.1898 0.4202 0.1646
0.750 0.8921 0.01182 0.00359 -0.1887 0.4064 0.1661
1.000 0.9145 0.01199 0.00371 -0.1876 0.3947 0.1680
1.250 0.9375 0.01214 0.00384 -0.1867 0.3855 0.1698
1.750 0.9824 0.01246 0.00411 -0.1845 0.3709 0.1740
2.000 1.0037 0.01262 0.00426 -0.1833 0.3647 0.1762
2.250 1.0247 0.01279 0.00442 -0.1819 0.3598 0.1786
2.500 1.0465 0.01293 0.00457 -0.1807 0.3555 0.1811
2.750 1.0680 0.01308 0.00475 -0.1795 0.3511 0.1859
3.000 1.0891 0.01328 0.00495 -0.1782 0.3473 0.1914
3.250 1.1103 0.01348 0.00517 -0.1769 0.3438 0.1990
3.500 1.1326 0.01363 0.00540 -0.1759 0.3408 0.2131
3.750 1.1546 0.01379 0.00564 -0.1749 0.3376 0.2358
4.000 1.1760 0.01398 0.00590 -0.1737 0.3347 0.2617
4.250 1.1965 0.01421 0.00619 -0.1724 0.3311 0.2874
4.500 1.2170 0.01445 0.00648 -0.1712 0.3275 0.3110
4.750 1.2390 0.01462 0.00676 -0.1702 0.3245 0.3419
5.000 1.2605 0.01480 0.00707 -0.1691 0.3219 0.3878
5.250 1.2815 0.01501 0.00742 -0.1680 0.3190 0.4403
5.500 1.3018 0.01527 0.00778 -0.1667 0.3162 0.4788
5.750 1.3214 0.01558 0.00815 -0.1654 0.3136 0.5076
6.000 1.3416 0.01587 0.00852 -0.1641 0.3113 0.5337
6.250 1.3631 0.01610 0.00885 -0.1631 0.3092 0.5561
6.500 1.3840 0.01636 0.00920 -0.1620 0.3070 0.5765
6.750 1.4046 0.01663 0.00957 -0.1609 0.3048 0.6012
7.000 1.4250 0.01687 0.00999 -0.1598 0.3027 0.6423
7.500 1.4630 0.01723 0.01079 -0.1571 0.2948 1.0000
7.750 1.4835 0.01755 0.01116 -0.1561 0.2884 1.0000
8.000 1.5015 0.01802 0.01163 -0.1546 0.2823 1.0000
8.250 1.5209 0.01842 0.01207 -0.1535 0.2749 1.0000
8.500 1.5378 0.01896 0.01258 -0.1520 0.2654 1.0000
8.750 1.5564 0.01942 0.01307 -0.1507 0.2547 1.0000
9.000 1.5709 0.02014 0.01371 -0.1490 0.2326 1.0000
9.250 1.5684 0.02211 0.01520 -0.1452 0.1661 1.0000
9.500 1.5766 0.02343 0.01639 -0.1428 0.1438 1.0000
9.750 1.5859 0.02468 0.01756 -0.1407 0.1247 1.0000
10.000 1.5944 0.02603 0.01879 -0.1385 0.1013 1.0000
10.250 1.5856 0.02882 0.02116 -0.1346 0.0454 1.0000
10.500 1.5871 0.03080 0.02304 -0.1319 0.0254 1.0000
10.750 1.5949 0.03228 0.02453 -0.1300 0.0190 1.0000
11.000 1.6036 0.03369 0.02598 -0.1282 0.0159 1.0000
11.250 1.6133 0.03505 0.02739 -0.1265 0.0142 1.0000
11.500 1.6208 0.03662 0.02903 -0.1248 0.0128 1.0000
11.750 1.6293 0.03814 0.03062 -0.1232 0.0118 1.0000
12.000 1.6373 0.03972 0.03229 -0.1216 0.0110 1.0000
12.250 1.6444 0.04143 0.03408 -0.1201 0.0104 1.0000
12.500 1.6497 0.04337 0.03609 -0.1185 0.0097 1.0000
12.750 1.6525 0.04561 0.03842 -0.1169 0.0092 1.0000
13.000 1.6569 0.04773 0.04063 -0.1155 0.0089 1.0000
13.250 1.6613 0.04993 0.04292 -0.1143 0.0085 1.0000
13.500 1.6645 0.05231 0.04542 -0.1131 0.0081 1.0000
13.750 1.6663 0.05492 0.04812 -0.1120 0.0078 1.0000
14.000 1.6674 0.05770 0.05100 -0.1110 0.0074 1.0000
14.250 1.6667 0.06078 0.05417 -0.1101 0.0072 1.0000
14.500 1.6632 0.06435 0.05786 -0.1095 0.0069 1.0000
14.750 1.6565 0.06854 0.06217 -0.1090 0.0067 1.0000
15.000 1.6532 0.07240 0.06615 -0.1089 0.0066 1.0000
15.250 1.6488 0.07658 0.07046 -0.1090 0.0064 1.0000
15.500 1.6425 0.08122 0.07524 -0.1094 0.0063 1.0000
15.750 1.6358 0.08615 0.08030 -0.1102 0.0062 1.0000
16.000 1.6282 0.09138 0.08567 -0.1114 0.0061 1.0000
16.250 1.6203 0.09678 0.09120 -0.1128 0.0060 1.0000
16.500 1.6121 0.10228 0.09684 -0.1143 0.0058 1.0000
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Polar data table (+)
Polar graphs
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