GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 359 AIRFOIL (goe359-il) Reynolds number: 200,000 Max Cl/Cd: 83.4 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe359-il-200000.txt Download as CSV file: xf-goe359-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 359 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2807 0.10880 0.10548 -0.0301 1.0000 0.0268
-8.250 -0.2817 0.10692 0.10366 -0.0305 1.0000 0.0269
-8.000 -0.2843 0.10508 0.10190 -0.0304 1.0000 0.0269
-7.750 -0.2839 0.10285 0.09975 -0.0312 1.0000 0.0269
-7.500 -0.2835 0.10063 0.09760 -0.0320 1.0000 0.0270
-7.250 -0.1930 0.08028 0.07754 -0.0299 0.9943 0.0296
-6.500 -0.2622 0.08557 0.08271 -0.0282 0.9938 0.0292
-6.250 -0.2318 0.08115 0.07827 -0.0353 0.9866 0.0311
-6.000 -0.1978 0.07651 0.07359 -0.0441 0.9778 0.0332
-5.750 -0.1398 0.07185 0.06881 -0.0625 0.9661 0.0356
-5.500 -0.0861 0.06680 0.06359 -0.0762 0.9585 0.0360
-5.250 -0.0671 0.06026 0.05706 -0.0791 0.9493 0.0369
-5.000 -0.0435 0.05647 0.05327 -0.0807 0.9420 0.0383
-4.750 -0.0096 0.05286 0.04959 -0.0856 0.9326 0.0411
-4.500 0.0601 0.04885 0.04512 -0.0997 0.9212 0.0472
-4.250 0.0848 0.04316 0.03941 -0.1030 0.9104 0.0487
-4.000 0.1116 0.04048 0.03667 -0.1047 0.8984 0.0512
-3.500 0.1781 0.03449 0.03021 -0.1109 0.8710 0.0632
-3.250 0.2136 0.03191 0.02717 -0.1136 0.8571 0.0738
-3.000 0.2344 0.03025 0.02553 -0.1132 0.8428 0.0777
-2.750 0.2631 0.02835 0.02333 -0.1141 0.8292 0.0889
-2.500 0.2897 0.02692 0.02170 -0.1145 0.8156 0.1024
-2.250 0.3165 0.02555 0.02010 -0.1147 0.8023 0.1161
-2.000 0.3428 0.02424 0.01861 -0.1148 0.7891 0.1304
-1.750 0.3684 0.02300 0.01723 -0.1147 0.7760 0.1460
-1.500 0.3954 0.02233 0.01632 -0.1146 0.7631 0.1727
-1.000 0.4648 0.01673 0.00934 -0.1138 0.7416 0.0797
-0.750 0.4937 0.01583 0.00800 -0.1131 0.7291 0.0720
-0.500 0.5208 0.01493 0.00693 -0.1126 0.7164 0.0707
-0.250 0.5477 0.01442 0.00625 -0.1120 0.7031 0.0713
0.000 0.5745 0.01404 0.00574 -0.1115 0.6900 0.0723
0.250 0.6011 0.01359 0.00521 -0.1109 0.6774 0.0721
0.500 0.6277 0.01327 0.00481 -0.1104 0.6654 0.0724
0.750 0.6543 0.01299 0.00448 -0.1100 0.6537 0.0738
1.000 0.6808 0.01282 0.00430 -0.1096 0.6414 0.0771
1.250 0.7075 0.01278 0.00421 -0.1092 0.6295 0.0826
1.500 0.7342 0.01275 0.00417 -0.1088 0.6181 0.0980
1.750 0.7537 0.01125 0.00431 -0.1073 0.6080 0.7704
2.000 0.7866 0.01114 0.00423 -0.1080 0.5965 1.0000
2.250 0.8132 0.01132 0.00430 -0.1076 0.5864 1.0000
2.500 0.8399 0.01153 0.00438 -0.1073 0.5778 1.0000
2.750 0.8664 0.01172 0.00448 -0.1070 0.5686 1.0000
3.000 0.8928 0.01192 0.00462 -0.1066 0.5597 1.0000
3.250 0.9191 0.01212 0.00473 -0.1063 0.5504 1.0000
3.500 0.9448 0.01227 0.00485 -0.1058 0.5390 1.0000
3.750 0.9704 0.01243 0.00498 -0.1053 0.5274 1.0000
4.000 0.9960 0.01261 0.00511 -0.1048 0.5165 1.0000
4.250 1.0217 0.01281 0.00527 -0.1044 0.5065 1.0000
4.500 1.0473 0.01300 0.00547 -0.1039 0.4960 1.0000
4.750 1.0725 0.01318 0.00566 -0.1034 0.4843 1.0000
5.000 1.0971 0.01337 0.00583 -0.1028 0.4707 1.0000
5.250 1.1207 0.01355 0.00596 -0.1020 0.4521 1.0000
5.500 1.1437 0.01374 0.00612 -0.1011 0.4304 1.0000
5.750 1.1668 0.01399 0.00631 -0.1002 0.4094 1.0000
6.000 1.1901 0.01427 0.00656 -0.0995 0.3909 1.0000
6.250 1.2121 0.01458 0.00683 -0.0985 0.3595 1.0000
6.500 1.2326 0.01504 0.00712 -0.0974 0.3187 1.0000
6.750 1.2519 0.01569 0.00754 -0.0962 0.2795 1.0000
7.000 1.2709 0.01641 0.00808 -0.0950 0.2506 1.0000
7.250 1.2905 0.01711 0.00867 -0.0939 0.2272 1.0000
7.500 1.3094 0.01785 0.00932 -0.0927 0.2031 1.0000
7.750 1.3280 0.01861 0.00995 -0.0914 0.1704 1.0000
8.000 1.3419 0.01977 0.01078 -0.0896 0.1232 1.0000
8.250 1.3506 0.02138 0.01201 -0.0872 0.0655 1.0000
8.500 1.3649 0.02244 0.01301 -0.0853 0.0530 1.0000
8.750 1.3806 0.02332 0.01396 -0.0836 0.0423 1.0000
9.000 1.3898 0.02467 0.01524 -0.0811 0.0247 1.0000
9.250 1.4005 0.02573 0.01638 -0.0787 0.0227 1.0000
9.500 1.4108 0.02676 0.01755 -0.0763 0.0218 1.0000
9.750 1.4198 0.02791 0.01887 -0.0738 0.0212 1.0000
10.000 1.4265 0.02926 0.02040 -0.0713 0.0208 1.0000
10.250 1.4308 0.03084 0.02218 -0.0689 0.0205 1.0000
10.500 1.4325 0.03273 0.02426 -0.0666 0.0203 1.0000
10.750 1.4322 0.03495 0.02665 -0.0647 0.0202 1.0000
11.000 1.4303 0.03748 0.02938 -0.0631 0.0202 1.0000
11.250 1.4270 0.04033 0.03239 -0.0618 0.0202 1.0000
11.500 1.4228 0.04344 0.03565 -0.0608 0.0201 1.0000
11.750 1.4185 0.04668 0.03903 -0.0601 0.0200 1.0000
12.000 1.4142 0.05003 0.04251 -0.0595 0.0198 1.0000
12.250 1.4099 0.05342 0.04603 -0.0590 0.0196 1.0000
12.500 1.4062 0.05679 0.04951 -0.0584 0.0194 1.0000
12.750 1.4033 0.06005 0.05289 -0.0578 0.0192 1.0000
13.000 1.4018 0.06310 0.05604 -0.0570 0.0193 1.0000
13.250 1.4027 0.06583 0.05886 -0.0559 0.0194 1.0000
13.500 1.4062 0.06821 0.06133 -0.0543 0.0195 1.0000
13.750 1.4128 0.07026 0.06348 -0.0524 0.0198 1.0000
14.000 1.4291 0.07145 0.06473 -0.0489 0.0202 1.0000
14.250 1.4371 0.07366 0.06706 -0.0481 0.0206 1.0000
14.500 1.4405 0.07640 0.06999 -0.0479 0.0211 1.0000
14.750 1.4442 0.07958 0.07353 -0.0470 0.0223 1.0000
15.000 1.4441 0.08394 0.07828 -0.0455 0.0241 1.0000
15.250 1.4413 0.08871 0.08330 -0.0446 0.0254 1.0000
15.500 1.1903 0.09371 0.08837 -0.0349 0.0206 1.0000
15.750 1.1817 0.09653 0.09135 -0.0350 0.0209 1.0000
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Polar data table (+)
Polar graphs
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