GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 100,000 Max Cl/Cd: 56.91 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe328-il-100000.txt Download as CSV file: xf-goe328-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 328 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3495 0.09759 0.09270 -0.0214 1.0000 0.0694
-7.500 -0.3498 0.09565 0.09084 -0.0244 1.0000 0.0712
-7.250 -0.3465 0.09450 0.08973 -0.0341 1.0000 0.0724
-7.000 -0.3390 0.09303 0.08822 -0.0423 1.0000 0.0729
-6.750 -0.3350 0.08662 0.08196 -0.0364 1.0000 0.0739
-6.500 -0.3298 0.08302 0.07843 -0.0326 1.0000 0.0753
-6.250 -0.3270 0.08045 0.07592 -0.0308 1.0000 0.0769
-6.000 -0.3277 0.07838 0.07392 -0.0297 1.0000 0.0789
-5.750 -0.3308 0.07658 0.07217 -0.0287 1.0000 0.0811
-5.500 -0.3328 0.07487 0.07047 -0.0289 1.0000 0.0837
-5.250 -0.3161 0.07563 0.07085 -0.0398 1.0000 0.0875
-5.000 -0.3193 0.07069 0.06610 -0.0360 1.0000 0.0884
-4.750 -0.3193 0.06775 0.06326 -0.0331 1.0000 0.0895
-4.500 -0.3116 0.06517 0.06071 -0.0321 0.9992 0.0916
-4.250 -0.2665 0.06127 0.05665 -0.0402 0.9927 0.0990
-4.000 -0.2174 0.05653 0.05169 -0.0495 0.9851 0.1052
-3.500 -0.1269 0.04917 0.04404 -0.0625 0.9704 0.1250
-3.250 -0.0859 0.04600 0.04068 -0.0679 0.9613 0.1374
-3.000 -0.0397 0.04291 0.03742 -0.0738 0.9561 0.1529
-2.750 -0.0001 0.04116 0.03541 -0.0779 0.9469 0.1763
-2.500 0.0413 0.03778 0.03203 -0.0824 0.9419 0.1979
-2.250 0.0755 0.03562 0.02982 -0.0850 0.9333 0.2299
-1.750 0.1402 0.03130 0.02564 -0.0883 0.9184 0.3500
-1.500 0.1728 0.02907 0.02351 -0.0890 0.9115 0.4118
-1.250 0.2020 0.02717 0.02165 -0.0891 0.9012 0.4484
-1.000 0.3056 0.02562 0.01773 -0.1005 0.8954 0.1494
-0.750 0.3411 0.02460 0.01615 -0.0999 0.8841 0.1164
-0.500 0.3735 0.02297 0.01442 -0.1001 0.8741 0.1095
-0.250 0.4057 0.02198 0.01323 -0.0999 0.8642 0.1083
0.000 0.4334 0.02124 0.01235 -0.0990 0.8513 0.1076
0.250 0.4611 0.02056 0.01151 -0.0980 0.8387 0.1053
0.500 0.4880 0.01989 0.01079 -0.0968 0.8259 0.1052
0.750 0.5141 0.01922 0.01012 -0.0955 0.8126 0.1067
1.000 0.5393 0.01862 0.00954 -0.0939 0.7984 0.1099
1.250 0.5640 0.01822 0.00907 -0.0923 0.7831 0.1171
1.500 0.5891 0.01773 0.00858 -0.0909 0.7673 0.1289
1.750 0.6153 0.01736 0.00816 -0.0897 0.7512 0.1478
2.000 0.6383 0.01518 0.00775 -0.0875 0.7360 1.0000
2.250 0.6642 0.01526 0.00754 -0.0864 0.7189 1.0000
2.500 0.6900 0.01536 0.00745 -0.0854 0.7016 1.0000
2.750 0.7160 0.01548 0.00742 -0.0845 0.6843 1.0000
3.000 0.7421 0.01563 0.00743 -0.0837 0.6672 1.0000
3.250 0.7683 0.01581 0.00748 -0.0830 0.6504 1.0000
3.500 0.7946 0.01602 0.00756 -0.0823 0.6338 1.0000
3.750 0.8207 0.01627 0.00774 -0.0817 0.6167 1.0000
4.000 0.8467 0.01655 0.00796 -0.0812 0.5995 1.0000
4.250 0.8728 0.01684 0.00819 -0.0807 0.5829 1.0000
4.500 0.8989 0.01715 0.00845 -0.0802 0.5672 1.0000
4.750 0.9251 0.01749 0.00877 -0.0798 0.5523 1.0000
5.000 0.9514 0.01786 0.00910 -0.0794 0.5381 1.0000
5.250 0.9777 0.01825 0.00947 -0.0790 0.5248 1.0000
5.500 1.0042 0.01868 0.00988 -0.0786 0.5124 1.0000
5.750 1.0300 0.01918 0.01043 -0.0783 0.4994 1.0000
6.000 1.0557 0.01973 0.01104 -0.0780 0.4872 1.0000
6.250 1.0817 0.02032 0.01168 -0.0777 0.4763 1.0000
6.500 1.1074 0.02082 0.01220 -0.0773 0.4644 1.0000
6.750 1.1322 0.02122 0.01261 -0.0766 0.4498 1.0000
7.000 1.1557 0.02155 0.01298 -0.0758 0.4326 1.0000
7.250 1.1783 0.02175 0.01324 -0.0747 0.4130 1.0000
7.500 1.2005 0.02188 0.01334 -0.0736 0.3927 1.0000
7.750 1.2205 0.02197 0.01358 -0.0722 0.3697 1.0000
8.000 1.2395 0.02199 0.01371 -0.0707 0.3435 1.0000
8.250 1.2531 0.02202 0.01384 -0.0683 0.2883 1.0000
8.500 1.2450 0.02514 0.01562 -0.0641 0.1158 1.0000
8.750 1.2466 0.02784 0.01811 -0.0609 0.0915 1.0000
9.000 1.2502 0.02996 0.02024 -0.0580 0.0818 1.0000
9.250 1.2574 0.03163 0.02203 -0.0554 0.0750 1.0000
9.500 1.2580 0.03362 0.02397 -0.0523 0.0704 1.0000
9.750 1.2636 0.03538 0.02580 -0.0495 0.0669 1.0000
10.000 1.2745 0.03712 0.02758 -0.0473 0.0639 1.0000
10.250 1.2917 0.03900 0.02941 -0.0458 0.0609 1.0000
10.500 1.3274 0.04181 0.03208 -0.0466 0.0571 1.0000
10.750 1.3488 0.04386 0.03436 -0.0457 0.0549 1.0000
11.000 1.3750 0.04651 0.03721 -0.0454 0.0536 1.0000
11.250 1.3965 0.04945 0.04042 -0.0446 0.0529 1.0000
11.500 1.4102 0.05245 0.04374 -0.0432 0.0522 1.0000
11.750 1.4193 0.05539 0.04695 -0.0415 0.0512 1.0000
12.000 1.4284 0.05846 0.05022 -0.0400 0.0501 1.0000
12.250 1.4326 0.06182 0.05383 -0.0382 0.0495 1.0000
12.500 1.4192 0.06488 0.05728 -0.0345 0.0500 1.0000
12.750 1.4002 0.06832 0.06112 -0.0314 0.0506 1.0000
13.000 1.3794 0.07232 0.06547 -0.0293 0.0513 1.0000
13.250 1.3579 0.07686 0.07035 -0.0282 0.0520 1.0000
13.500 1.3351 0.08190 0.07569 -0.0282 0.0527 1.0000
13.750 1.3111 0.08750 0.08154 -0.0291 0.0533 1.0000
14.000 1.2859 0.09369 0.08798 -0.0310 0.0540 1.0000
14.250 1.2599 0.10050 0.09500 -0.0339 0.0546 1.0000
14.500 1.2332 0.10806 0.10275 -0.0378 0.0552 1.0000
14.750 1.2067 0.11632 0.11117 -0.0426 0.0559 1.0000
15.000 1.1830 0.12503 0.12000 -0.0476 0.0568 1.0000
15.250 1.1859 0.13049 0.12551 -0.0481 0.0585 1.0000
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Polar data table (+)
Polar graphs
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