GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.7 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe431-il-1000000-n5.txt Download as CSV file: xf-goe431-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.3021 0.09857 0.09642 -0.1031 0.9551 0.0059
-14.000 -0.3028 0.09083 0.08856 -0.1108 0.9498 0.0059
-13.750 -0.2991 0.08346 0.08105 -0.1193 0.9421 0.0060
-13.500 -0.2855 0.07710 0.07457 -0.1285 0.9350 0.0060
-13.250 -0.2690 0.07173 0.06906 -0.1370 0.9224 0.0060
-12.750 -0.2512 0.06338 0.06039 -0.1476 0.8858 0.0063
-12.500 -0.2537 0.05980 0.05667 -0.1500 0.8689 0.0063
-12.250 -0.2523 0.05707 0.05386 -0.1515 0.8566 0.0064
-11.750 -0.2596 0.05096 0.04760 -0.1543 0.8369 0.0065
-11.500 -0.2654 0.04811 0.04469 -0.1551 0.8292 0.0066
-11.250 -0.2752 0.04532 0.04186 -0.1556 0.8225 0.0066
-11.000 -0.2827 0.04135 0.03781 -0.1594 0.8160 0.0067
-10.750 -0.2833 0.03678 0.03316 -0.1655 0.8110 0.0067
-10.500 -0.2773 0.03051 0.02676 -0.1756 0.8061 0.0069
-10.250 -0.2593 0.02206 0.01801 -0.1898 0.8018 0.0069
-10.000 -0.2315 0.01766 0.01333 -0.1967 0.7990 0.0071
-9.750 -0.2037 0.01637 0.01191 -0.1987 0.7969 0.0074
-9.500 -0.1758 0.01535 0.01078 -0.2001 0.7948 0.0076
-9.250 -0.1480 0.01453 0.00985 -0.2011 0.7922 0.0079
-9.000 -0.1203 0.01385 0.00906 -0.2019 0.7892 0.0082
-8.750 -0.0926 0.01326 0.00836 -0.2025 0.7859 0.0084
-8.250 -0.0368 0.01200 0.00689 -0.2037 0.7803 0.0093
-8.000 -0.0086 0.01154 0.00637 -0.2041 0.7774 0.0098
-7.750 0.0196 0.01116 0.00592 -0.2044 0.7746 0.0104
-7.500 0.0478 0.01082 0.00550 -0.2047 0.7720 0.0109
-7.250 0.0759 0.01054 0.00515 -0.2048 0.7692 0.0114
-7.000 0.1041 0.01017 0.00469 -0.2051 0.7663 0.0127
-6.750 0.1326 0.00986 0.00434 -0.2053 0.7637 0.0139
-6.500 0.1610 0.00961 0.00404 -0.2055 0.7606 0.0150
-6.250 0.1894 0.00933 0.00372 -0.2056 0.7575 0.0174
-6.000 0.2177 0.00908 0.00343 -0.2058 0.7544 0.0215
-5.750 0.2458 0.00881 0.00316 -0.2059 0.7513 0.0303
-5.500 0.2743 0.00856 0.00292 -0.2061 0.7483 0.0388
-5.250 0.3027 0.00835 0.00270 -0.2062 0.7447 0.0461
-5.000 0.3310 0.00819 0.00251 -0.2062 0.7406 0.0532
-4.750 0.3590 0.00794 0.00226 -0.2063 0.7366 0.0679
-4.500 0.3872 0.00764 0.00213 -0.2065 0.7334 0.1198
-4.250 0.4156 0.00761 0.00210 -0.2065 0.7295 0.1256
-4.000 0.4438 0.00763 0.00212 -0.2064 0.7251 0.1318
-3.750 0.4717 0.00767 0.00209 -0.2063 0.7207 0.1341
-3.500 0.5000 0.00765 0.00204 -0.2062 0.7165 0.1355
-3.250 0.5281 0.00759 0.00197 -0.2062 0.7108 0.1380
-3.000 0.5555 0.00758 0.00192 -0.2059 0.7046 0.1397
-2.750 0.5835 0.00755 0.00187 -0.2059 0.6977 0.1407
-2.500 0.6104 0.00757 0.00184 -0.2056 0.6881 0.1421
-2.250 0.6368 0.00761 0.00181 -0.2051 0.6730 0.1435
-2.000 0.6600 0.00779 0.00183 -0.2040 0.6356 0.1450
-1.750 0.6655 0.00891 0.00226 -0.1996 0.4927 0.1455
-1.500 0.6877 0.00921 0.00238 -0.1985 0.4585 0.1461
-1.250 0.7115 0.00941 0.00245 -0.1976 0.4340 0.1466
-1.000 0.7357 0.00958 0.00252 -0.1969 0.4146 0.1471
-0.750 0.7604 0.00973 0.00258 -0.1962 0.3990 0.1476
-0.500 0.7853 0.00986 0.00265 -0.1956 0.3867 0.1481
-0.250 0.8101 0.00999 0.00271 -0.1949 0.3760 0.1485
0.000 0.8354 0.01009 0.00277 -0.1944 0.3674 0.1489
0.250 0.8602 0.01022 0.00285 -0.1937 0.3598 0.1492
0.500 0.8857 0.01029 0.00290 -0.1932 0.3539 0.1505
0.750 0.9106 0.01038 0.00297 -0.1926 0.3480 0.1520
1.000 0.9355 0.01048 0.00305 -0.1920 0.3432 0.1538
1.250 0.9607 0.01056 0.00314 -0.1914 0.3393 0.1555
1.500 0.9854 0.01066 0.00323 -0.1908 0.3354 0.1571
1.750 1.0096 0.01077 0.00334 -0.1900 0.3314 0.1586
2.000 1.0337 0.01089 0.00345 -0.1892 0.3278 0.1601
2.250 1.0582 0.01098 0.00356 -0.1885 0.3253 0.1616
2.500 1.0820 0.01108 0.00367 -0.1877 0.3225 0.1631
2.750 1.1047 0.01119 0.00378 -0.1867 0.3200 0.1644
3.000 1.1268 0.01131 0.00391 -0.1855 0.3175 0.1663
3.250 1.1479 0.01146 0.00406 -0.1841 0.3134 0.1702
3.500 1.1701 0.01158 0.00421 -0.1830 0.3106 0.1744
3.750 1.1928 0.01170 0.00436 -0.1820 0.3082 0.1790
4.000 1.2153 0.01183 0.00453 -0.1810 0.3056 0.1868
4.250 1.2374 0.01197 0.00473 -0.1799 0.3033 0.2011
4.500 1.2593 0.01211 0.00494 -0.1788 0.3013 0.2277
4.750 1.2807 0.01228 0.00517 -0.1777 0.2985 0.2551
5.000 1.3020 0.01246 0.00541 -0.1765 0.2956 0.2778
5.250 1.3243 0.01259 0.00562 -0.1755 0.2940 0.3004
5.500 1.3463 0.01274 0.00585 -0.1745 0.2925 0.3242
5.750 1.3682 0.01289 0.00611 -0.1734 0.2908 0.3568
6.000 1.3896 0.01304 0.00639 -0.1724 0.2891 0.4140
6.250 1.4106 0.01322 0.00670 -0.1712 0.2870 0.4636
6.500 1.4303 0.01348 0.00701 -0.1698 0.2827 0.4976
6.750 1.4510 0.01372 0.00731 -0.1686 0.2773 0.5197
7.000 1.4710 0.01398 0.00761 -0.1674 0.2715 0.5403
7.250 1.4898 0.01431 0.00796 -0.1659 0.2650 0.5568
7.500 1.5099 0.01459 0.00828 -0.1647 0.2581 0.5709
7.750 1.5274 0.01500 0.00869 -0.1631 0.2470 0.5845
8.000 1.5419 0.01560 0.00921 -0.1610 0.2243 0.6020
8.250 1.5381 0.01733 0.01057 -0.1564 0.1597 0.6267
8.750 1.5634 0.01859 0.01218 -0.1523 0.1244 1.0000
9.000 1.5753 0.01955 0.01301 -0.1501 0.1039 1.0000
9.250 1.5748 0.02143 0.01455 -0.1465 0.0554 1.0000
9.500 1.5775 0.02311 0.01607 -0.1433 0.0265 1.0000
9.750 1.5881 0.02422 0.01714 -0.1413 0.0173 1.0000
10.000 1.6014 0.02512 0.01805 -0.1396 0.0141 1.0000
10.250 1.6144 0.02606 0.01901 -0.1379 0.0121 1.0000
10.500 1.6283 0.02694 0.01993 -0.1364 0.0111 1.0000
10.750 1.6407 0.02795 0.02096 -0.1347 0.0100 1.0000
11.000 1.6526 0.02902 0.02206 -0.1331 0.0091 1.0000
11.250 1.6651 0.03004 0.02313 -0.1316 0.0086 1.0000
11.500 1.6769 0.03114 0.02428 -0.1300 0.0080 1.0000
11.750 1.6872 0.03236 0.02554 -0.1284 0.0074 1.0000
12.000 1.6969 0.03368 0.02690 -0.1268 0.0068 1.0000
12.250 1.7067 0.03501 0.02828 -0.1252 0.0065 1.0000
12.500 1.7167 0.03635 0.02968 -0.1238 0.0062 1.0000
12.750 1.7253 0.03784 0.03123 -0.1223 0.0059 1.0000
13.000 1.7337 0.03937 0.03282 -0.1208 0.0057 1.0000
13.250 1.7406 0.04108 0.03459 -0.1193 0.0054 1.0000
13.500 1.7467 0.04293 0.03649 -0.1179 0.0052 1.0000
13.750 1.7510 0.04500 0.03863 -0.1164 0.0049 1.0000
14.000 1.7553 0.04712 0.04082 -0.1151 0.0048 1.0000
14.250 1.7605 0.04920 0.04298 -0.1139 0.0046 1.0000
14.500 1.7646 0.05145 0.04531 -0.1127 0.0045 1.0000
14.750 1.7673 0.05393 0.04788 -0.1117 0.0043 1.0000
15.000 1.7700 0.05649 0.05052 -0.1108 0.0042 1.0000
15.250 1.7714 0.05927 0.05338 -0.1099 0.0040 1.0000
15.500 1.7712 0.06233 0.05653 -0.1092 0.0039 1.0000
15.750 1.7706 0.06556 0.05984 -0.1087 0.0038 1.0000
16.000 1.7677 0.06922 0.06360 -0.1084 0.0037 1.0000
16.250 1.7638 0.07316 0.06764 -0.1083 0.0036 1.0000
16.500 1.7569 0.07772 0.07230 -0.1086 0.0035 1.0000
16.750 1.7487 0.08267 0.07738 -0.1092 0.0034 1.0000
17.000 1.7397 0.08795 0.08278 -0.1102 0.0033 1.0000
17.250 1.7323 0.09312 0.08807 -0.1114 0.0033 1.0000
17.500 1.7239 0.09855 0.09362 -0.1129 0.0033 1.0000
17.750 1.7153 0.10407 0.09926 -0.1145 0.0032 1.0000
18.000 1.7062 0.10973 0.10504 -0.1164 0.0032 1.0000
18.250 1.6974 0.11533 0.11076 -0.1183 0.0032 1.0000
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