GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 448 AIRFOIL (goe448-il) Reynolds number: 200,000 Max Cl/Cd: 74.49 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe448-il-200000-n5.txt Download as CSV file: xf-goe448-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 448 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2346 0.09753 0.09279 -0.1382 0.7843 0.0331
-9.500 0.2426 0.09541 0.09067 -0.1400 0.7794 0.0362
-9.250 0.2478 0.09306 0.08830 -0.1422 0.7748 0.0366
-9.000 0.2555 0.09053 0.08573 -0.1437 0.7709 0.0366
-8.750 0.2638 0.08798 0.08317 -0.1450 0.7666 0.0366
-8.500 0.2727 0.08542 0.08061 -0.1461 0.7621 0.0366
-8.250 0.2885 0.08344 0.07861 -0.1455 0.7583 0.0380
-8.000 0.2977 0.08172 0.07684 -0.1474 0.7545 0.0421
-7.750 0.3032 0.07951 0.07464 -0.1495 0.7499 0.0424
-7.500 0.3101 0.07729 0.07242 -0.1506 0.7452 0.0424
-7.250 0.3186 0.07504 0.07016 -0.1515 0.7412 0.0423
-7.000 0.3325 0.07269 0.06775 -0.1508 0.7382 0.0400
-6.750 0.3432 0.07048 0.06554 -0.1530 0.7341 0.0411
-6.500 0.3550 0.06786 0.06292 -0.1569 0.7295 0.0421
-6.250 0.3688 0.06570 0.06073 -0.1579 0.7256 0.0412
-6.000 0.3849 0.06317 0.05814 -0.1608 0.7222 0.0407
-5.750 0.4019 0.06064 0.05558 -0.1641 0.7185 0.0408
-5.500 0.4241 0.05711 0.05200 -0.1712 0.7142 0.0423
-5.250 0.4452 0.05445 0.04928 -0.1747 0.7103 0.0422
-5.000 0.4711 0.05133 0.04605 -0.1798 0.7070 0.0423
-4.750 0.4963 0.04896 0.04361 -0.1833 0.7038 0.0429
-4.500 0.5147 0.04806 0.04272 -0.1834 0.6995 0.0439
-4.250 0.5400 0.04621 0.04082 -0.1863 0.6957 0.0453
-4.000 0.5712 0.04344 0.03793 -0.1912 0.6924 0.0456
-3.750 0.6065 0.04049 0.03480 -0.1967 0.6895 0.0460
-3.500 0.6413 0.03749 0.03165 -0.2020 0.6858 0.0468
-3.250 0.6817 0.03366 0.02760 -0.2086 0.6819 0.0492
-3.000 0.7099 0.03237 0.02622 -0.2104 0.6784 0.0501
-2.500 0.7921 0.02537 0.01845 -0.2207 0.6729 0.0559
-2.000 0.8522 0.02200 0.01445 -0.2238 0.6653 0.0629
-1.750 0.8787 0.02169 0.01405 -0.2240 0.6618 0.0648
-1.500 0.9104 0.02061 0.01248 -0.2253 0.6589 0.0700
-1.250 0.9390 0.02039 0.01223 -0.2259 0.6561 0.0719
-1.000 0.9626 0.02014 0.01189 -0.2255 0.6520 0.0749
-0.750 0.9893 0.01981 0.01125 -0.2255 0.6481 0.0779
-0.500 1.0157 0.01937 0.01079 -0.2257 0.6448 0.0800
-0.250 1.0440 0.01914 0.01046 -0.2261 0.6418 0.0820
0.000 1.0710 0.01890 0.01011 -0.2262 0.6386 0.0834
0.250 1.0942 0.01878 0.00992 -0.2256 0.6344 0.0846
0.500 1.1190 0.01870 0.00975 -0.2253 0.6307 0.0864
0.750 1.1457 0.01862 0.00955 -0.2252 0.6273 0.0876
1.000 1.1749 0.01840 0.00922 -0.2257 0.6243 0.0883
1.250 1.1956 0.01837 0.00923 -0.2247 0.6197 0.0891
1.500 1.2177 0.01833 0.00921 -0.2239 0.6145 0.0899
1.750 1.2435 0.01824 0.00908 -0.2237 0.6100 0.0909
2.000 1.2665 0.01827 0.00911 -0.2231 0.6053 0.0925
2.250 1.2862 0.01837 0.00926 -0.2218 0.6001 0.0940
2.500 1.3096 0.01842 0.00931 -0.2213 0.5959 0.0952
2.750 1.3361 0.01844 0.00929 -0.2213 0.5925 0.0961
3.000 1.3555 0.01862 0.00952 -0.2200 0.5883 0.0970
3.250 1.3731 0.01881 0.00975 -0.2184 0.5838 0.0978
3.500 1.3941 0.01896 0.00990 -0.2174 0.5798 0.0988
3.750 1.4191 0.01905 0.00996 -0.2172 0.5763 0.1002
4.000 1.4353 0.01935 0.01033 -0.2154 0.5717 0.1019
4.250 1.4528 0.01966 0.01070 -0.2139 0.5669 0.1041
4.500 1.4742 0.01988 0.01093 -0.2131 0.5627 0.1083
5.000 1.5119 0.02053 0.01170 -0.2106 0.5542 0.1235
5.250 1.5293 0.02089 0.01216 -0.2092 0.5492 0.1567
5.500 1.5507 0.02112 0.01244 -0.2085 0.5446 0.2155
5.750 1.5651 0.02157 0.01311 -0.2068 0.5388 0.3141
6.000 1.5760 0.02133 0.01370 -0.2042 0.5330 1.0000
6.250 1.5952 0.02170 0.01400 -0.2031 0.5279 1.0000
6.500 1.6060 0.02243 0.01479 -0.2008 0.5219 1.0000
6.750 1.6203 0.02305 0.01541 -0.1991 0.5163 1.0000
7.000 1.6386 0.02350 0.01583 -0.1980 0.5118 1.0000
7.250 1.6490 0.02435 0.01675 -0.1959 0.5060 1.0000
7.500 1.6616 0.02510 0.01753 -0.1940 0.5003 1.0000
7.750 1.6784 0.02563 0.01802 -0.1928 0.4950 1.0000
8.000 1.6847 0.02677 0.01926 -0.1902 0.4879 1.0000
8.250 1.6966 0.02758 0.02005 -0.1884 0.4807 1.0000
8.500 1.7009 0.02888 0.02139 -0.1857 0.4713 1.0000
8.750 1.7073 0.03004 0.02251 -0.1833 0.4611 1.0000
9.000 1.7099 0.03152 0.02400 -0.1806 0.4496 1.0000
9.250 1.7125 0.03310 0.02561 -0.1780 0.4383 1.0000
9.500 1.7176 0.03456 0.02705 -0.1758 0.4285 1.0000
9.750 1.7216 0.03617 0.02867 -0.1735 0.4183 1.0000
10.000 1.7252 0.03789 0.03041 -0.1713 0.4081 1.0000
10.250 1.7276 0.03972 0.03221 -0.1691 0.3973 1.0000
10.500 1.7272 0.04183 0.03430 -0.1667 0.3848 1.0000
10.750 1.7270 0.04404 0.03651 -0.1644 0.3722 1.0000
11.000 1.7275 0.04623 0.03872 -0.1623 0.3611 1.0000
11.250 1.7268 0.04858 0.04104 -0.1602 0.3502 1.0000
11.500 1.7247 0.05113 0.04359 -0.1581 0.3375 1.0000
11.750 1.7213 0.05387 0.04631 -0.1560 0.3240 1.0000
12.000 1.7162 0.05686 0.04928 -0.1539 0.3097 1.0000
12.250 1.7104 0.06000 0.05240 -0.1519 0.2945 1.0000
12.500 1.7020 0.06348 0.05584 -0.1499 0.2763 1.0000
12.750 1.6899 0.06745 0.05973 -0.1478 0.2534 1.0000
13.000 1.6701 0.07239 0.06454 -0.1455 0.2202 1.0000
13.250 1.6413 0.07852 0.07045 -0.1430 0.1852 1.0000
13.500 1.6222 0.08364 0.07546 -0.1412 0.1661 1.0000
13.750 1.6087 0.08819 0.07998 -0.1398 0.1511 1.0000
14.000 1.5975 0.09255 0.08431 -0.1386 0.1346 1.0000
14.250 1.5747 0.09849 0.09009 -0.1373 0.0964 1.0000
14.500 1.5468 0.10520 0.09660 -0.1363 0.0666 1.0000
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Polar data table (+)
Polar graphs
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