GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 100,000 Max Cl/Cd: 49.02 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe11k-il-100000-n5.txt Download as CSV file: xf-goe11k-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 11K 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5057 0.09235 0.08763 -0.0301 1.0000 0.0247
-8.000 -0.5187 0.08972 0.08507 -0.0286 1.0000 0.0245
-7.750 -0.5301 0.08697 0.08239 -0.0275 1.0000 0.0243
-7.500 -0.5384 0.08346 0.07892 -0.0276 1.0000 0.0241
-7.250 -0.5445 0.07972 0.07520 -0.0278 1.0000 0.0240
-7.000 -0.5486 0.07578 0.07126 -0.0283 1.0000 0.0238
-6.750 -0.5510 0.07118 0.06662 -0.0291 1.0000 0.0239
-6.500 -0.5488 0.06622 0.06158 -0.0305 0.9996 0.0239
-6.250 -0.5312 0.05924 0.05436 -0.0357 0.9959 0.0243
-6.000 -0.5134 0.05186 0.04661 -0.0394 0.9922 0.0249
-5.750 -0.4967 0.04492 0.03921 -0.0417 0.9887 0.0253
-5.500 -0.4793 0.03971 0.03350 -0.0427 0.9859 0.0260
-5.250 -0.4600 0.03682 0.03024 -0.0427 0.9828 0.0272
-5.000 -0.4365 0.03490 0.02798 -0.0430 0.9800 0.0299
-4.750 -0.4126 0.03130 0.02371 -0.0429 0.9779 0.0326
-4.500 -0.3896 0.02790 0.01943 -0.0418 0.9758 0.0362
-4.250 -0.3662 0.02694 0.01830 -0.0414 0.9730 0.0400
-4.000 -0.3398 0.02560 0.01638 -0.0409 0.9707 0.0474
-3.750 -0.3128 0.02467 0.01533 -0.0411 0.9685 0.0541
-3.500 -0.2837 0.02388 0.01426 -0.0415 0.9667 0.0638
-3.250 -0.2605 0.02318 0.01333 -0.0407 0.9635 0.0720
-3.000 -0.2355 0.02275 0.01274 -0.0404 0.9607 0.0804
-2.750 -0.2090 0.02221 0.01220 -0.0404 0.9583 0.0875
-2.500 -0.1803 0.02179 0.01158 -0.0407 0.9561 0.0933
-2.250 -0.1510 0.02127 0.01104 -0.0412 0.9543 0.0973
-2.000 -0.1299 0.02091 0.01065 -0.0400 0.9506 0.1011
-1.750 -0.1058 0.02068 0.01032 -0.0394 0.9475 0.1062
-1.500 -0.0796 0.02046 0.01011 -0.0393 0.9448 0.1139
-1.250 -0.0509 0.02031 0.00990 -0.0396 0.9424 0.1217
-1.000 -0.0205 0.02013 0.00973 -0.0404 0.9405 0.1347
-0.750 0.0010 0.01994 0.00961 -0.0393 0.9369 0.1563
-0.500 0.0951 0.01775 0.01005 -0.0543 0.9445 1.0000
-0.250 0.1244 0.01796 0.01006 -0.0549 0.9421 1.0000
0.000 0.1546 0.01818 0.01013 -0.0556 0.9400 1.0000
0.250 0.1732 0.01832 0.01017 -0.0540 0.9347 1.0000
0.500 0.1992 0.01851 0.01027 -0.0539 0.9312 1.0000
0.750 0.2292 0.01871 0.01040 -0.0546 0.9281 1.0000
1.000 0.2646 0.01888 0.01051 -0.0564 0.9251 1.0000
1.250 0.2848 0.01897 0.01057 -0.0550 0.9174 1.0000
1.500 0.3193 0.01905 0.01065 -0.0564 0.9128 1.0000
1.750 0.3491 0.01915 0.01075 -0.0569 0.9075 1.0000
2.000 0.3756 0.01923 0.01087 -0.0567 0.9006 1.0000
2.250 0.4122 0.01926 0.01095 -0.0585 0.8965 1.0000
2.500 0.4354 0.01934 0.01109 -0.0576 0.8882 1.0000
2.750 0.4723 0.01924 0.01110 -0.0592 0.8824 1.0000
3.000 0.5031 0.01899 0.01095 -0.0594 0.8707 1.0000
3.250 0.5517 0.01788 0.01001 -0.0619 0.8532 1.0000
3.500 0.5928 0.01640 0.00864 -0.0623 0.8224 1.0000
4.000 0.6373 0.01556 0.00801 -0.0579 0.7530 1.0000
4.250 0.7318 0.01493 0.00638 -0.0690 0.4831 1.0000
4.500 0.7414 0.01613 0.00695 -0.0654 0.3607 1.0000
4.750 0.7506 0.01753 0.00753 -0.0621 0.2107 1.0000
5.000 0.7671 0.01859 0.00822 -0.0602 0.1512 1.0000
5.250 0.7854 0.01936 0.00895 -0.0584 0.1298 1.0000
5.500 0.8031 0.02012 0.00968 -0.0565 0.1137 1.0000
5.750 0.8205 0.02089 0.01041 -0.0547 0.0968 1.0000
6.000 0.8377 0.02169 0.01120 -0.0529 0.0824 1.0000
6.250 0.8552 0.02251 0.01211 -0.0511 0.0683 1.0000
6.500 0.8720 0.02347 0.01313 -0.0491 0.0550 1.0000
6.750 0.8896 0.02450 0.01424 -0.0472 0.0441 1.0000
7.000 0.9079 0.02565 0.01545 -0.0455 0.0376 1.0000
7.250 0.9274 0.02672 0.01664 -0.0440 0.0323 1.0000
7.500 0.9483 0.02843 0.01843 -0.0430 0.0293 1.0000
7.750 0.9731 0.03023 0.02053 -0.0424 0.0259 1.0000
8.000 0.9971 0.03238 0.02296 -0.0417 0.0239 1.0000
8.250 1.0169 0.03448 0.02531 -0.0405 0.0224 1.0000
8.500 1.0318 0.03686 0.02794 -0.0387 0.0208 1.0000
8.750 1.0437 0.04006 0.03159 -0.0363 0.0197 1.0000
9.000 1.0511 0.04317 0.03521 -0.0330 0.0191 1.0000
9.250 1.0531 0.04642 0.03892 -0.0292 0.0188 1.0000
9.500 1.0495 0.04983 0.04275 -0.0248 0.0186 1.0000
9.750 1.0409 0.05314 0.04643 -0.0200 0.0185 1.0000
10.000 1.0278 0.05635 0.04995 -0.0149 0.0184 1.0000
10.250 1.0120 0.05966 0.05354 -0.0102 0.0184 1.0000
10.500 0.9946 0.06312 0.05724 -0.0061 0.0185 1.0000
10.750 0.9750 0.06690 0.06124 -0.0029 0.0185 1.0000
11.000 0.9532 0.07114 0.06569 -0.0008 0.0184 1.0000
11.250 0.9312 0.07587 0.07058 -0.0001 0.0186 1.0000
11.500 0.9103 0.08108 0.07592 -0.0009 0.0189 1.0000
11.750 0.8876 0.08769 0.08265 -0.0038 0.0190 1.0000
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Polar data table (+)
Polar graphs
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