GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 491 AIRFOIL (goe491-il) Reynolds number: 100,000 Max Cl/Cd: 48.88 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe491-il-100000.txt Download as CSV file: xf-goe491-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 491 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4995 0.11349 0.10839 -0.0020 1.0000 0.0563
-8.750 -0.5028 0.11190 0.10687 -0.0052 1.0000 0.0567
-8.500 -0.5068 0.11001 0.10505 -0.0082 1.0000 0.0568
-8.250 -0.5058 0.10770 0.10277 -0.0118 1.0000 0.0570
-8.000 -0.5014 0.10493 0.10004 -0.0152 1.0000 0.0571
-7.750 -0.4845 0.09508 0.09021 -0.0064 1.0000 0.0593
-7.500 -0.4789 0.09161 0.08677 -0.0062 1.0000 0.0606
-7.250 -0.4738 0.08829 0.08348 -0.0071 1.0000 0.0621
-7.000 -0.4682 0.08505 0.08027 -0.0086 1.0000 0.0638
-6.750 -0.4617 0.08175 0.07696 -0.0106 1.0000 0.0659
-6.500 -0.4527 0.07867 0.07386 -0.0139 1.0000 0.0684
-6.250 -0.4353 0.07757 0.07252 -0.0221 1.0000 0.0706
-6.000 -0.4280 0.07201 0.06702 -0.0217 1.0000 0.0716
-5.750 -0.4226 0.06766 0.06280 -0.0181 1.0000 0.0747
-5.500 -0.4102 0.06447 0.05958 -0.0184 1.0000 0.0790
-5.250 -0.3822 0.06389 0.05847 -0.0245 1.0000 0.0849
-5.000 -0.3765 0.05764 0.05247 -0.0223 1.0000 0.0865
-4.750 -0.3647 0.05426 0.04912 -0.0210 1.0000 0.0896
-4.500 -0.3371 0.05337 0.04765 -0.0235 1.0000 0.0988
-4.250 -0.3284 0.04804 0.04257 -0.0218 1.0000 0.1011
-4.000 -0.3071 0.04641 0.04064 -0.0216 1.0000 0.1118
-3.750 -0.2943 0.04232 0.03658 -0.0205 1.0000 0.1157
-3.500 -0.2765 0.03990 0.03399 -0.0197 1.0000 0.1289
-3.250 -0.2612 0.03743 0.03149 -0.0183 1.0000 0.1451
-3.000 -0.2442 0.03520 0.02917 -0.0170 1.0000 0.1630
-2.750 -0.2278 0.03298 0.02683 -0.0155 1.0000 0.1872
-2.500 -0.1841 0.02899 0.02134 -0.0142 1.0000 0.0986
-2.250 -0.1640 0.02561 0.01789 -0.0129 1.0000 0.0957
-2.000 -0.1409 0.02335 0.01519 -0.0113 1.0000 0.0961
-1.750 -0.1166 0.02138 0.01263 -0.0095 1.0000 0.0979
-1.500 -0.0948 0.02010 0.01115 -0.0082 1.0000 0.1119
-1.250 -0.0724 0.01887 0.00979 -0.0072 1.0000 0.1251
-1.000 -0.0490 0.01770 0.00855 -0.0062 1.0000 0.1326
-0.750 -0.0263 0.01702 0.00775 -0.0051 1.0000 0.1428
-0.500 -0.0031 0.01635 0.00705 -0.0041 1.0000 0.1478
-0.250 0.0195 0.01590 0.00653 -0.0031 1.0000 0.1536
0.000 0.0410 0.01540 0.00616 -0.0021 1.0000 0.1606
0.250 0.0615 0.01510 0.00595 -0.0010 1.0000 0.1738
0.500 0.0829 0.01488 0.00581 -0.0001 1.0000 0.1866
0.750 0.1237 0.01458 0.00567 -0.0033 0.9925 0.2253
1.000 0.2135 0.01255 0.00538 -0.0156 0.9901 1.0000
1.250 0.2822 0.01263 0.00538 -0.0242 0.9697 1.0000
1.500 0.3486 0.01241 0.00518 -0.0318 0.9449 1.0000
1.750 0.4168 0.01199 0.00482 -0.0393 0.9142 1.0000
2.000 0.4761 0.01163 0.00448 -0.0444 0.8622 1.0000
2.250 0.5124 0.01160 0.00429 -0.0448 0.7921 1.0000
2.500 0.5397 0.01182 0.00426 -0.0436 0.7293 1.0000
2.750 0.5638 0.01219 0.00439 -0.0421 0.6804 1.0000
3.000 0.5870 0.01261 0.00466 -0.0407 0.6417 1.0000
3.250 0.6100 0.01303 0.00495 -0.0394 0.6096 1.0000
3.500 0.6319 0.01343 0.00521 -0.0378 0.5766 1.0000
3.750 0.6530 0.01380 0.00546 -0.0361 0.5412 1.0000
4.000 0.6742 0.01418 0.00576 -0.0345 0.5086 1.0000
4.250 0.6955 0.01458 0.00608 -0.0329 0.4768 1.0000
4.500 0.7169 0.01499 0.00646 -0.0314 0.4471 1.0000
4.750 0.7376 0.01537 0.00682 -0.0299 0.4139 1.0000
5.000 0.7583 0.01571 0.00716 -0.0283 0.3808 1.0000
5.250 0.7787 0.01593 0.00751 -0.0266 0.3391 1.0000
5.500 0.7967 0.01634 0.00776 -0.0246 0.2465 1.0000
5.750 0.8075 0.01855 0.00898 -0.0219 0.1222 1.0000
6.000 0.8248 0.01994 0.01023 -0.0198 0.1014 1.0000
6.250 0.8424 0.02134 0.01157 -0.0179 0.0908 1.0000
6.500 0.8609 0.02278 0.01295 -0.0162 0.0803 1.0000
6.750 0.8824 0.02445 0.01479 -0.0146 0.0749 1.0000
7.000 0.9034 0.02636 0.01665 -0.0134 0.0681 1.0000
7.250 0.9255 0.02855 0.01910 -0.0120 0.0635 1.0000
7.500 0.9475 0.03105 0.02194 -0.0105 0.0610 1.0000
7.750 0.9672 0.03357 0.02471 -0.0090 0.0580 1.0000
8.000 0.9825 0.03780 0.02907 -0.0078 0.0547 1.0000
8.250 0.9955 0.04107 0.03290 -0.0056 0.0543 1.0000
8.500 1.0069 0.04550 0.03776 -0.0037 0.0549 1.0000
8.750 1.0086 0.04860 0.04187 0.0000 0.0581 1.0000
9.000 1.0007 0.05465 0.04857 0.0027 0.0622 1.0000
9.250 1.0004 0.06029 0.05441 0.0040 0.0654 1.0000
9.500 0.9882 0.07380 0.06842 0.0040 0.0923 1.0000
9.750 0.9546 0.07741 0.07239 0.0047 0.0917 1.0000
10.000 0.9225 0.08170 0.07679 0.0044 0.0914 1.0000
10.250 0.8917 0.08821 0.08335 -0.0006 0.0912 1.0000
10.500 0.8106 0.11422 0.10911 -0.0267 0.1506 1.0000
10.750 0.8539 0.11770 0.11279 -0.0188 0.1453 1.0000
11.000 0.8154 0.12330 0.11816 -0.0278 0.1435 1.0000
11.250 0.8043 0.12774 0.12254 -0.0314 0.1381 1.0000
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Polar data table (+)
Polar graphs
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