GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 100,000 Max Cl/Cd: 56.67 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe477-il-100000.txt Download as CSV file: xf-goe477-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 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 -0.4043 0.10434 0.10017 -0.0201 1.0000 0.0906
-7.500 -0.4245 0.10344 0.09935 -0.0183 1.0000 0.0910
-7.250 -0.4487 0.10258 0.09857 -0.0198 1.0000 0.0917
-7.000 -0.4629 0.10049 0.09648 -0.0247 1.0000 0.0923
-6.750 -0.4572 0.09569 0.09176 -0.0182 1.0000 0.0940
-6.500 -0.4519 0.09320 0.08928 -0.0140 1.0000 0.0965
-6.250 -0.4534 0.09077 0.08687 -0.0132 1.0000 0.0992
-6.000 -0.4324 0.08593 0.08173 -0.0343 0.9936 0.1070
-5.750 -0.4240 0.08103 0.07698 -0.0302 0.9913 0.1086
-5.500 -0.4105 0.07823 0.07421 -0.0280 0.9883 0.1118
-5.250 -0.3824 0.07308 0.06874 -0.0412 0.9839 0.1228
-5.000 -0.3736 0.07044 0.06624 -0.0367 0.9810 0.1260
-4.750 -0.3489 0.06639 0.06192 -0.0440 0.9762 0.1385
-4.500 -0.3334 0.06374 0.05936 -0.0422 0.9733 0.1430
-4.250 -0.3056 0.05999 0.05540 -0.0473 0.9699 0.1558
-4.000 -0.2853 0.05722 0.05242 -0.0498 0.9653 0.1699
-3.750 -0.2631 0.05472 0.04982 -0.0512 0.9614 0.1856
-3.500 -0.2368 0.05208 0.04707 -0.0530 0.9582 0.2018
-3.250 -0.1729 0.04090 0.03419 -0.0628 0.9559 0.1230
-3.000 -0.1514 0.03821 0.03132 -0.0625 0.9515 0.1183
-2.750 -0.1207 0.03558 0.02816 -0.0635 0.9473 0.1177
-2.500 -0.0779 0.03347 0.02542 -0.0662 0.9423 0.1194
-2.250 -0.0496 0.03205 0.02357 -0.0664 0.9339 0.1240
-1.750 0.0309 0.03026 0.02125 -0.0705 0.9154 0.1360
-1.500 0.0696 0.02939 0.02025 -0.0724 0.9082 0.1410
-1.250 0.0993 0.02902 0.01981 -0.0728 0.9005 0.1487
-1.000 0.1431 0.02847 0.01920 -0.0755 0.8949 0.1565
-0.750 0.1658 0.02819 0.01890 -0.0746 0.8857 0.1638
-0.500 0.2135 0.02775 0.01852 -0.0778 0.8801 0.1814
-0.250 0.2345 0.02747 0.01834 -0.0765 0.8696 0.1981
0.000 0.2734 0.02667 0.01792 -0.0781 0.8616 0.2604
0.250 0.3533 0.02415 0.01723 -0.0868 0.8535 1.0000
0.500 0.3922 0.02403 0.01689 -0.0881 0.8419 1.0000
0.750 0.4572 0.02336 0.01603 -0.0936 0.8352 1.0000
1.000 0.4843 0.02335 0.01592 -0.0929 0.8233 1.0000
1.250 0.5230 0.02310 0.01558 -0.0941 0.8145 1.0000
1.500 0.5668 0.02258 0.01499 -0.0958 0.8065 1.0000
1.750 0.5947 0.02242 0.01478 -0.0950 0.7950 1.0000
2.000 0.6452 0.02152 0.01383 -0.0975 0.7894 1.0000
2.250 0.6701 0.02126 0.01355 -0.0961 0.7763 1.0000
2.500 0.6973 0.02086 0.01315 -0.0949 0.7633 1.0000
2.750 0.7263 0.02034 0.01262 -0.0939 0.7503 1.0000
3.000 0.7561 0.01968 0.01198 -0.0930 0.7365 1.0000
3.250 0.7846 0.01896 0.01127 -0.0917 0.7204 1.0000
3.500 0.8139 0.01813 0.01044 -0.0905 0.7022 1.0000
3.750 0.8379 0.01747 0.00981 -0.0886 0.6771 1.0000
4.000 0.8670 0.01672 0.00899 -0.0874 0.6453 1.0000
4.250 0.8966 0.01621 0.00825 -0.0863 0.6017 1.0000
4.500 0.9220 0.01627 0.00792 -0.0849 0.5512 1.0000
4.750 0.9432 0.01677 0.00805 -0.0833 0.5075 1.0000
5.000 0.9647 0.01745 0.00838 -0.0819 0.4754 1.0000
5.250 0.9872 0.01819 0.00891 -0.0809 0.4506 1.0000
5.500 1.0122 0.01899 0.00950 -0.0805 0.4319 1.0000
5.750 1.0374 0.01978 0.01016 -0.0801 0.4165 1.0000
6.000 1.0619 0.02052 0.01087 -0.0796 0.4034 1.0000
6.250 1.0866 0.02128 0.01163 -0.0792 0.3923 1.0000
6.500 1.1139 0.02209 0.01237 -0.0792 0.3833 1.0000
6.750 1.1372 0.02281 0.01323 -0.0786 0.3749 1.0000
7.000 1.1647 0.02364 0.01401 -0.0787 0.3679 1.0000
7.250 1.1848 0.02424 0.01479 -0.0775 0.3583 1.0000
7.500 1.2043 0.02478 0.01538 -0.0762 0.3470 1.0000
7.750 1.2235 0.02522 0.01582 -0.0749 0.3352 1.0000
8.000 1.2424 0.02561 0.01620 -0.0735 0.3237 1.0000
8.250 1.2570 0.02600 0.01681 -0.0714 0.3129 1.0000
8.500 1.2722 0.02637 0.01728 -0.0694 0.3019 1.0000
8.750 1.2842 0.02662 0.01760 -0.0669 0.2893 1.0000
9.000 1.2935 0.02686 0.01792 -0.0639 0.2763 1.0000
9.250 1.2952 0.02707 0.01826 -0.0598 0.2609 1.0000
9.500 1.2907 0.02734 0.01869 -0.0547 0.2439 1.0000
9.750 1.2846 0.02789 0.01933 -0.0499 0.2215 1.0000
10.000 1.2820 0.02881 0.02027 -0.0460 0.1832 1.0000
10.250 1.2724 0.03106 0.02187 -0.0424 0.0990 1.0000
10.500 1.2663 0.03370 0.02423 -0.0393 0.0820 1.0000
10.750 1.2635 0.03607 0.02662 -0.0367 0.0751 1.0000
11.000 1.2600 0.03848 0.02915 -0.0343 0.0703 1.0000
11.250 1.2520 0.04128 0.03202 -0.0320 0.0673 1.0000
11.500 1.2488 0.04378 0.03467 -0.0301 0.0650 1.0000
11.750 1.2465 0.04630 0.03735 -0.0284 0.0631 1.0000
12.000 1.2446 0.04890 0.04005 -0.0269 0.0614 1.0000
12.250 1.2443 0.05144 0.04268 -0.0255 0.0597 1.0000
12.500 1.2470 0.05388 0.04507 -0.0240 0.0572 1.0000
12.750 1.2679 0.05534 0.04643 -0.0225 0.0546 1.0000
13.000 1.2890 0.05684 0.04804 -0.0213 0.0529 1.0000
13.250 1.3180 0.05840 0.04971 -0.0204 0.0516 1.0000
13.500 1.3421 0.06052 0.05200 -0.0196 0.0503 1.0000
13.750 1.3603 0.06302 0.05462 -0.0190 0.0485 1.0000
14.000 1.3824 0.06605 0.05777 -0.0186 0.0469 1.0000
14.250 1.3913 0.06947 0.06143 -0.0177 0.0468 1.0000
14.500 1.3883 0.07300 0.06525 -0.0167 0.0469 1.0000
14.750 1.3795 0.07672 0.06928 -0.0158 0.0472 1.0000
15.000 1.3661 0.08081 0.07368 -0.0152 0.0476 1.0000
15.250 1.3439 0.08555 0.07875 -0.0154 0.0480 1.0000
15.500 1.3194 0.09090 0.08442 -0.0163 0.0484 1.0000
15.750 1.2923 0.09698 0.09081 -0.0183 0.0490 1.0000
16.000 1.2654 0.10373 0.09784 -0.0213 0.0496 1.0000
16.250 1.2371 0.11147 0.10584 -0.0254 0.0501 1.0000
16.500 1.2070 0.12037 0.11498 -0.0309 0.0507 1.0000
16.750 1.1757 0.13049 0.12531 -0.0376 0.0516 1.0000
17.000 1.1416 0.14231 0.13730 -0.0457 0.0526 1.0000
17.250 1.1081 0.15534 0.15043 -0.0544 0.0539 1.0000
17.500 1.0948 0.16430 0.15939 -0.0590 0.0552 1.0000
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