GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 410 AIRFOIL (goe410-il) Reynolds number: 100,000 Max Cl/Cd: 35.27 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe410-il-100000-n5.txt Download as CSV file: xf-goe410-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 410 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0000 0.09115 0.08440 -0.0179 1.0000 0.0864
-15.750 -1.0637 0.07795 0.07081 -0.0260 1.0000 0.0874
-15.500 -1.0411 0.07810 0.07108 -0.0251 1.0000 0.0891
-15.250 -1.0497 0.07386 0.06676 -0.0272 1.0000 0.0906
-15.000 -1.0672 0.06855 0.06127 -0.0299 1.0000 0.0921
-14.750 -1.0853 0.06343 0.05595 -0.0323 1.0000 0.0936
-14.500 -1.1030 0.05867 0.05093 -0.0342 1.0000 0.0952
-14.250 -1.1204 0.05429 0.04624 -0.0356 1.0000 0.0968
-14.000 -1.1120 0.05262 0.04461 -0.0356 1.0000 0.0985
-13.750 -1.1063 0.05084 0.04281 -0.0356 1.0000 0.1002
-13.500 -1.1047 0.04873 0.04060 -0.0357 1.0000 0.1021
-13.250 -1.1059 0.04647 0.03819 -0.0355 1.0000 0.1041
-13.000 -1.1083 0.04421 0.03572 -0.0351 1.0000 0.1061
-12.750 -1.1093 0.04220 0.03350 -0.0343 1.0000 0.1081
-12.500 -1.0966 0.04112 0.03248 -0.0337 1.0000 0.1100
-12.250 -1.0882 0.03994 0.03127 -0.0327 1.0000 0.1122
-12.000 -1.0821 0.03869 0.02992 -0.0314 1.0000 0.1146
-11.750 -1.0778 0.03741 0.02849 -0.0298 1.0000 0.1172
-11.500 -1.0760 0.03620 0.02703 -0.0275 1.0000 0.1196
-11.250 -1.0589 0.03528 0.02622 -0.0266 1.0000 0.1220
-11.000 -1.0445 0.03441 0.02533 -0.0254 1.0000 0.1246
-10.750 -1.0301 0.03347 0.02433 -0.0242 1.0000 0.1274
-10.500 -1.0155 0.03250 0.02322 -0.0229 1.0000 0.1301
-10.250 -1.0002 0.03155 0.02208 -0.0217 1.0000 0.1326
-10.000 -0.9790 0.03056 0.02116 -0.0211 1.0000 0.1350
-9.750 -0.9593 0.02970 0.02034 -0.0203 1.0000 0.1376
-9.500 -0.9401 0.02888 0.01949 -0.0193 1.0000 0.1405
-9.250 -0.9208 0.02807 0.01862 -0.0184 1.0000 0.1436
-9.000 -0.9011 0.02731 0.01774 -0.0174 1.0000 0.1465
-8.750 -0.8804 0.02645 0.01695 -0.0166 1.0000 0.1494
-8.500 -0.8609 0.02567 0.01623 -0.0156 1.0000 0.1527
-8.250 -0.8415 0.02496 0.01553 -0.0146 1.0000 0.1566
-8.000 -0.8217 0.02430 0.01483 -0.0135 1.0000 0.1607
-7.750 -0.8025 0.02360 0.01416 -0.0124 1.0000 0.1646
-7.500 -0.7846 0.02287 0.01353 -0.0111 1.0000 0.1688
-7.250 -0.7662 0.02223 0.01292 -0.0098 1.0000 0.1737
-7.000 -0.7475 0.02166 0.01235 -0.0085 1.0000 0.1793
-6.750 -0.7317 0.02097 0.01180 -0.0069 1.0000 0.1854
-6.500 -0.7154 0.02040 0.01129 -0.0053 1.0000 0.1928
-6.250 -0.6976 0.01979 0.01080 -0.0042 0.9959 0.2015
-6.000 -0.6604 0.01908 0.01023 -0.0067 0.9690 0.2176
-5.750 -0.6242 0.01842 0.00973 -0.0089 0.9426 0.2429
-5.500 -0.5893 0.01786 0.00935 -0.0107 0.9159 0.2784
-5.250 -0.5574 0.01749 0.00908 -0.0116 0.8884 0.3130
-5.000 -0.5277 0.01727 0.00888 -0.0117 0.8630 0.3416
-4.750 -0.5009 0.01715 0.00872 -0.0112 0.8390 0.3643
-4.500 -0.4755 0.01709 0.00860 -0.0104 0.8163 0.3835
-4.250 -0.4505 0.01705 0.00850 -0.0095 0.7951 0.4007
-4.000 -0.4253 0.01704 0.00838 -0.0086 0.7753 0.4168
-3.750 -0.4000 0.01703 0.00833 -0.0078 0.7565 0.4301
-3.500 -0.3744 0.01701 0.00825 -0.0070 0.7388 0.4418
-3.250 -0.3486 0.01699 0.00810 -0.0063 0.7224 0.4545
-3.000 -0.3227 0.01699 0.00806 -0.0055 0.7072 0.4657
-2.750 -0.2963 0.01695 0.00795 -0.0050 0.6920 0.4762
-2.500 -0.2696 0.01692 0.00787 -0.0045 0.6782 0.4858
-2.250 -0.2431 0.01689 0.00775 -0.0039 0.6659 0.4957
-2.000 -0.2163 0.01686 0.00769 -0.0034 0.6534 0.5053
-1.750 -0.1894 0.01681 0.00757 -0.0030 0.6422 0.5138
-1.500 -0.1625 0.01678 0.00753 -0.0024 0.6318 0.5224
-1.250 -0.1355 0.01676 0.00745 -0.0021 0.6215 0.5325
-1.000 -0.1087 0.01674 0.00744 -0.0015 0.6123 0.5417
-0.750 -0.0816 0.01673 0.00738 -0.0012 0.6028 0.5518
-0.500 -0.0545 0.01671 0.00740 -0.0007 0.5941 0.5600
-0.250 -0.0272 0.01672 0.00735 -0.0004 0.5863 0.5698
0.000 0.0000 0.01671 0.00740 0.0000 0.5776 0.5776
0.250 0.0272 0.01672 0.00735 0.0004 0.5699 0.5863
0.500 0.0545 0.01671 0.00740 0.0007 0.5600 0.5941
0.750 0.0816 0.01673 0.00739 0.0012 0.5519 0.6028
1.000 0.1087 0.01674 0.00744 0.0015 0.5416 0.6122
1.250 0.1355 0.01676 0.00744 0.0021 0.5325 0.6215
1.500 0.1625 0.01678 0.00752 0.0025 0.5223 0.6318
1.750 0.1894 0.01681 0.00757 0.0030 0.5138 0.6422
2.000 0.2163 0.01686 0.00769 0.0034 0.5053 0.6534
2.250 0.2431 0.01689 0.00776 0.0039 0.4957 0.6659
2.500 0.2696 0.01692 0.00787 0.0045 0.4858 0.6782
2.750 0.2963 0.01695 0.00795 0.0050 0.4762 0.6920
3.000 0.3227 0.01699 0.00806 0.0055 0.4657 0.7072
3.250 0.3486 0.01699 0.00810 0.0063 0.4545 0.7225
3.500 0.3744 0.01701 0.00825 0.0070 0.4418 0.7388
3.750 0.4000 0.01703 0.00833 0.0078 0.4301 0.7566
4.000 0.4253 0.01704 0.00838 0.0086 0.4168 0.7753
4.250 0.4505 0.01705 0.00850 0.0095 0.4008 0.7951
4.500 0.4755 0.01709 0.00860 0.0104 0.3836 0.8163
4.750 0.5009 0.01715 0.00872 0.0112 0.3644 0.8390
5.000 0.5277 0.01727 0.00888 0.0117 0.3416 0.8630
5.250 0.5574 0.01749 0.00908 0.0115 0.3129 0.8884
5.500 0.5893 0.01786 0.00935 0.0107 0.2783 0.9160
5.750 0.6242 0.01842 0.00973 0.0089 0.2428 0.9426
6.000 0.6604 0.01908 0.01023 0.0067 0.2176 0.9690
6.250 0.6977 0.01978 0.01080 0.0042 0.2016 0.9960
6.500 0.7153 0.02040 0.01129 0.0053 0.1927 1.0000
6.750 0.7317 0.02097 0.01180 0.0069 0.1853 1.0000
7.000 0.7476 0.02166 0.01235 0.0085 0.1793 1.0000
7.250 0.7662 0.02223 0.01292 0.0098 0.1738 1.0000
7.500 0.7846 0.02287 0.01353 0.0111 0.1688 1.0000
7.750 0.8025 0.02359 0.01416 0.0124 0.1646 1.0000
8.000 0.8218 0.02430 0.01483 0.0135 0.1607 1.0000
8.250 0.8416 0.02496 0.01553 0.0146 0.1566 1.0000
8.500 0.8610 0.02567 0.01623 0.0156 0.1527 1.0000
8.750 0.8805 0.02645 0.01695 0.0166 0.1493 1.0000
9.000 0.9012 0.02731 0.01774 0.0174 0.1465 1.0000
9.250 0.9209 0.02807 0.01861 0.0184 0.1436 1.0000
9.500 0.9403 0.02888 0.01949 0.0193 0.1405 1.0000
9.750 0.9595 0.02970 0.02034 0.0202 0.1375 1.0000
10.000 0.9792 0.03056 0.02116 0.0211 0.1349 1.0000
10.250 1.0005 0.03155 0.02208 0.0216 0.1326 1.0000
10.500 1.0157 0.03250 0.02322 0.0229 0.1301 1.0000
10.750 1.0305 0.03347 0.02433 0.0241 0.1273 1.0000
11.000 1.0449 0.03441 0.02533 0.0253 0.1246 1.0000
11.250 1.0592 0.03528 0.02621 0.0265 0.1220 1.0000
11.500 1.0763 0.03620 0.02703 0.0275 0.1196 1.0000
11.750 1.0783 0.03741 0.02849 0.0297 0.1172 1.0000
12.000 1.0827 0.03869 0.02992 0.0314 0.1146 1.0000
12.250 1.0888 0.03994 0.03127 0.0326 0.1122 1.0000
12.500 1.0973 0.04112 0.03248 0.0336 0.1100 1.0000
12.750 1.1103 0.04219 0.03349 0.0343 0.1081 1.0000
13.000 1.1090 0.04421 0.03572 0.0350 0.1061 1.0000
13.250 1.1064 0.04647 0.03819 0.0355 0.1040 1.0000
13.500 1.1056 0.04871 0.04058 0.0356 0.1020 1.0000
13.750 1.1074 0.05081 0.04278 0.0355 0.1002 1.0000
14.000 1.1132 0.05260 0.04458 0.0355 0.0985 1.0000
14.250 1.1217 0.05425 0.04620 0.0355 0.0968 1.0000
14.500 1.1041 0.05866 0.05092 0.0341 0.0952 1.0000
14.750 1.0864 0.06342 0.05594 0.0321 0.0935 1.0000
15.000 1.0687 0.06847 0.06120 0.0298 0.0920 1.0000
15.250 1.0528 0.07356 0.06645 0.0272 0.0905 1.0000
15.500 1.0446 0.07776 0.07073 0.0252 0.0890 1.0000
15.750 1.0696 0.07728 0.07010 0.0263 0.0872 1.0000
16.000 0.9986 0.09159 0.08486 0.0174 0.0864 1.0000
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