GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.91 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe441-il-1000000-n5.txt Download as CSV file: xf-goe441-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 441 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4256 0.05377 0.05035 -0.1219 0.7701 0.0242
-12.250 -0.4665 0.04025 0.03659 -0.1403 0.7615 0.0242
-12.000 -0.4557 0.02775 0.02372 -0.1636 0.7546 0.0243
-11.750 -0.4192 0.02228 0.01794 -0.1769 0.7480 0.0244
-11.500 -0.3894 0.02040 0.01589 -0.1810 0.7411 0.0246
-11.250 -0.3599 0.01915 0.01452 -0.1834 0.7349 0.0248
-11.000 -0.3305 0.01819 0.01345 -0.1852 0.7280 0.0250
-10.750 -0.3013 0.01742 0.01257 -0.1866 0.7204 0.0251
-10.500 -0.2717 0.01674 0.01180 -0.1878 0.7147 0.0253
-10.250 -0.2421 0.01613 0.01112 -0.1889 0.7087 0.0255
-10.000 -0.2126 0.01561 0.01049 -0.1897 0.7017 0.0257
-9.750 -0.1829 0.01511 0.00991 -0.1906 0.6948 0.0259
-9.500 -0.1533 0.01467 0.00938 -0.1913 0.6852 0.0261
-9.250 -0.1238 0.01426 0.00887 -0.1919 0.6756 0.0263
-9.000 -0.0945 0.01390 0.00840 -0.1925 0.6618 0.0265
-8.750 -0.0653 0.01359 0.00796 -0.1930 0.6425 0.0267
-8.500 -0.0388 0.01354 0.00761 -0.1929 0.5798 0.0270
-8.000 0.0170 0.01333 0.00702 -0.1933 0.5213 0.0275
-7.750 0.0465 0.01310 0.00670 -0.1938 0.5117 0.0277
-7.500 0.0761 0.01290 0.00641 -0.1942 0.5041 0.0278
-7.250 0.1058 0.01267 0.00609 -0.1946 0.4979 0.0281
-7.000 0.1361 0.01236 0.00573 -0.1952 0.4937 0.0285
-6.750 0.1661 0.01212 0.00545 -0.1957 0.4891 0.0288
-6.500 0.1959 0.01195 0.00522 -0.1961 0.4842 0.0292
-6.000 0.2556 0.01164 0.00481 -0.1968 0.4757 0.0300
-5.750 0.2856 0.01149 0.00463 -0.1972 0.4723 0.0305
-5.500 0.3155 0.01136 0.00445 -0.1975 0.4689 0.0309
-5.250 0.3453 0.01125 0.00430 -0.1978 0.4654 0.0314
-5.000 0.3749 0.01117 0.00416 -0.1981 0.4618 0.0318
-4.750 0.4047 0.01105 0.00400 -0.1984 0.4584 0.0326
-4.500 0.4348 0.01092 0.00387 -0.1988 0.4560 0.0334
-4.250 0.4646 0.01083 0.00376 -0.1991 0.4531 0.0344
-4.000 0.4943 0.01076 0.00366 -0.1994 0.4498 0.0355
-3.750 0.5239 0.01070 0.00357 -0.1996 0.4467 0.0367
-3.500 0.5534 0.01064 0.00349 -0.1999 0.4437 0.0385
-3.250 0.5827 0.01061 0.00343 -0.2001 0.4404 0.0403
-3.000 0.6124 0.01055 0.00337 -0.2004 0.4383 0.0430
-2.750 0.6420 0.01050 0.00331 -0.2007 0.4361 0.0462
-2.500 0.6716 0.01045 0.00327 -0.2009 0.4334 0.0506
-2.250 0.7010 0.01041 0.00323 -0.2012 0.4304 0.0559
-2.000 0.7302 0.01039 0.00322 -0.2014 0.4275 0.0630
-1.750 0.7592 0.01038 0.00323 -0.2016 0.4247 0.0727
-1.500 0.7879 0.01042 0.00327 -0.2017 0.4217 0.0812
-1.250 0.8169 0.01044 0.00330 -0.2018 0.4197 0.0870
-1.000 0.8460 0.01045 0.00331 -0.2020 0.4174 0.0907
-0.750 0.8749 0.01047 0.00334 -0.2021 0.4148 0.0944
-0.500 0.9035 0.01052 0.00337 -0.2022 0.4122 0.0973
-0.250 0.9320 0.01057 0.00341 -0.2023 0.4096 0.1003
0.000 0.9603 0.01061 0.00345 -0.2023 0.4068 0.1050
0.250 0.9882 0.01070 0.00351 -0.2023 0.4034 0.1084
0.500 1.0168 0.01074 0.00355 -0.2024 0.4015 0.1108
0.750 1.0453 0.01076 0.00359 -0.2025 0.3995 0.1161
1.000 1.0736 0.01080 0.00364 -0.2026 0.3970 0.1203
1.500 1.1295 0.01093 0.00379 -0.2026 0.3912 0.1370
1.750 1.1573 0.01097 0.00391 -0.2027 0.3881 0.1782
2.000 1.1847 0.01106 0.00401 -0.2026 0.3853 0.1952
2.250 1.2125 0.01111 0.00410 -0.2027 0.3830 0.2075
2.500 1.2400 0.01119 0.00420 -0.2026 0.3800 0.2192
2.750 1.2672 0.01128 0.00431 -0.2025 0.3767 0.2325
3.250 1.3211 0.01143 0.00460 -0.2024 0.3702 0.3195
3.500 1.3483 0.01148 0.00477 -0.2024 0.3681 0.3773
3.750 1.3753 0.01156 0.00493 -0.2023 0.3659 0.4153
4.000 1.4018 0.01166 0.00509 -0.2022 0.3632 0.4405
4.250 1.4277 0.01180 0.00524 -0.2019 0.3601 0.4577
4.500 1.4530 0.01196 0.00541 -0.2015 0.3571 0.4718
4.750 1.4779 0.01213 0.00560 -0.2010 0.3542 0.4864
5.000 1.5029 0.01228 0.00579 -0.2006 0.3519 0.5027
5.250 1.5284 0.01241 0.00597 -0.2002 0.3499 0.5228
5.500 1.5534 0.01254 0.00616 -0.1998 0.3475 0.5491
5.750 1.5777 0.01269 0.00637 -0.1993 0.3447 0.5736
6.000 1.6002 0.01285 0.00661 -0.1984 0.3417 0.6130
6.250 1.6216 0.01300 0.00691 -0.1974 0.3384 0.6899
6.500 1.6448 0.01311 0.00719 -0.1968 0.3355 0.7871
7.000 1.6853 0.01328 0.00765 -0.1941 0.3301 1.0000
7.250 1.7068 0.01356 0.00793 -0.1931 0.3269 1.0000
7.500 1.7263 0.01394 0.00827 -0.1918 0.3217 1.0000
7.750 1.7474 0.01424 0.00857 -0.1909 0.3169 1.0000
8.000 1.7675 0.01459 0.00892 -0.1897 0.3116 1.0000
8.250 1.7855 0.01506 0.00935 -0.1883 0.3057 1.0000
8.500 1.8053 0.01544 0.00973 -0.1872 0.3003 1.0000
8.750 1.8234 0.01591 0.01018 -0.1859 0.2939 1.0000
9.000 1.8403 0.01645 0.01070 -0.1844 0.2877 1.0000
9.250 1.8580 0.01696 0.01120 -0.1831 0.2811 1.0000
9.500 1.8724 0.01766 0.01186 -0.1813 0.2734 1.0000
9.750 1.8878 0.01832 0.01250 -0.1798 0.2650 1.0000
10.000 1.9009 0.01912 0.01327 -0.1779 0.2572 1.0000
10.250 1.9151 0.01988 0.01402 -0.1763 0.2494 1.0000
10.500 1.9263 0.02084 0.01495 -0.1744 0.2413 1.0000
10.750 1.9367 0.02187 0.01595 -0.1724 0.2318 1.0000
11.000 1.9468 0.02295 0.01701 -0.1705 0.2236 1.0000
11.250 1.9530 0.02432 0.01834 -0.1682 0.2137 1.0000
11.500 1.9620 0.02553 0.01954 -0.1663 0.2052 1.0000
11.750 1.9669 0.02708 0.02106 -0.1641 0.1963 1.0000
12.000 1.9685 0.02893 0.02287 -0.1617 0.1855 1.0000
12.250 1.9687 0.03094 0.02485 -0.1593 0.1735 1.0000
12.500 1.9614 0.03367 0.02752 -0.1565 0.1577 1.0000
12.750 1.9333 0.03841 0.03212 -0.1525 0.1302 1.0000
13.000 1.9151 0.04256 0.03622 -0.1496 0.1142 1.0000
13.250 1.9031 0.04630 0.03997 -0.1475 0.1040 1.0000
13.500 1.8900 0.05031 0.04399 -0.1456 0.0942 1.0000
13.750 1.8609 0.05629 0.04996 -0.1435 0.0755 1.0000
14.000 1.8288 0.06300 0.05667 -0.1418 0.0582 1.0000
14.250 1.7993 0.06980 0.06354 -0.1408 0.0469 1.0000
14.500 1.7799 0.07555 0.06937 -0.1403 0.0410 1.0000
14.750 1.7658 0.08063 0.07454 -0.1400 0.0376 1.0000
15.000 1.7536 0.08550 0.07947 -0.1397 0.0350 1.0000
15.250 1.7417 0.09033 0.08439 -0.1396 0.0330 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 441 AIRFOIL (goe441-il)