GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 500,000 Max Cl/Cd: 97.82 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe92-il-500000-n5.txt Download as CSV file: xf-goe92-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1466 0.08954 0.08725 -0.0360 0.8708 0.0078
-8.750 -0.1424 0.08637 0.08407 -0.0367 0.8636 0.0081
-8.500 -0.1381 0.08314 0.08082 -0.0374 0.8565 0.0086
-8.250 -0.1337 0.07992 0.07759 -0.0386 0.8496 0.0091
-8.000 -0.1306 0.07692 0.07457 -0.0403 0.8418 0.0093
-7.750 -0.1273 0.07377 0.07141 -0.0418 0.8336 0.0094
-7.500 -0.1235 0.07057 0.06819 -0.0431 0.8247 0.0094
-7.250 -0.1191 0.06726 0.06487 -0.0445 0.8148 0.0094
-7.000 -0.1143 0.06389 0.06149 -0.0461 0.8053 0.0094
-6.750 -0.1086 0.06039 0.05797 -0.0483 0.7957 0.0094
-6.500 -0.0987 0.05657 0.05412 -0.0515 0.7850 0.0094
-6.250 -0.0869 0.05258 0.05008 -0.0549 0.7728 0.0094
-6.000 -0.0734 0.04854 0.04598 -0.0583 0.7581 0.0094
-5.750 -0.0584 0.04448 0.04182 -0.0616 0.7390 0.0094
-5.250 -0.0562 0.05552 0.05265 -0.0694 0.7509 0.0086
-5.000 -0.0308 0.05147 0.04842 -0.0737 0.7237 0.0076
-4.750 0.0025 0.04493 0.04159 -0.0800 0.6913 0.0067
-4.500 0.0286 0.04177 0.03813 -0.0825 0.6526 0.0068
-4.250 0.0553 0.03899 0.03509 -0.0846 0.6244 0.0070
-4.000 0.0834 0.03601 0.03187 -0.0865 0.6042 0.0072
-3.750 0.1120 0.03335 0.02898 -0.0880 0.5878 0.0081
-3.500 0.1427 0.02958 0.02489 -0.0894 0.5744 0.0087
-3.250 0.1731 0.02566 0.02059 -0.0901 0.5621 0.0089
-3.000 0.2035 0.02121 0.01563 -0.0904 0.5509 0.0096
-2.750 0.2306 0.02013 0.01434 -0.0904 0.5374 0.0103
-2.500 0.2583 0.01896 0.01292 -0.0904 0.5244 0.0118
-2.250 0.2877 0.01540 0.00872 -0.0898 0.5134 0.0141
-2.000 0.3147 0.01540 0.00860 -0.0898 0.4982 0.0150
-1.750 0.3419 0.01506 0.00809 -0.0897 0.4824 0.0172
-1.500 0.3701 0.01410 0.00672 -0.0892 0.4667 0.0199
-1.250 0.3968 0.01356 0.00605 -0.0892 0.4498 0.0215
-1.000 0.4237 0.01339 0.00576 -0.0891 0.4326 0.0230
-0.750 0.4508 0.01303 0.00522 -0.0889 0.4156 0.0244
-0.500 0.4778 0.01284 0.00487 -0.0888 0.3993 0.0265
-0.250 0.5049 0.01267 0.00454 -0.0886 0.3851 0.0276
0.000 0.5318 0.01258 0.00431 -0.0884 0.3715 0.0282
0.500 0.5853 0.01202 0.00356 -0.0881 0.3502 0.0297
0.750 0.6120 0.01184 0.00332 -0.0880 0.3425 0.0302
1.000 0.6392 0.01172 0.00316 -0.0879 0.3369 0.0300
1.250 0.6662 0.01165 0.00304 -0.0878 0.3315 0.0298
1.500 0.6932 0.01160 0.00294 -0.0877 0.3269 0.0299
1.750 0.7205 0.01152 0.00285 -0.0877 0.3233 0.0301
2.000 0.7477 0.01149 0.00279 -0.0876 0.3193 0.0308
2.250 0.7747 0.01151 0.00277 -0.0876 0.3154 0.0320
2.500 0.8018 0.01156 0.00279 -0.0875 0.3119 0.0338
2.750 0.8290 0.01160 0.00283 -0.0875 0.3080 0.0357
3.000 0.8560 0.01169 0.00288 -0.0874 0.3037 0.0372
3.250 0.8828 0.01181 0.00297 -0.0873 0.3003 0.0384
3.500 0.9096 0.01192 0.00309 -0.0873 0.2977 0.0432
3.750 0.9367 0.01199 0.00320 -0.0872 0.2952 0.0494
4.250 0.9882 0.01061 0.00367 -0.0871 0.2894 1.0000
4.500 1.0146 0.01079 0.00382 -0.0869 0.2864 1.0000
4.750 1.0408 0.01098 0.00399 -0.0868 0.2832 1.0000
5.000 1.0676 0.01112 0.00416 -0.0868 0.2805 1.0000
5.250 1.0939 0.01128 0.00432 -0.0867 0.2727 1.0000
5.500 1.1199 0.01148 0.00448 -0.0865 0.2625 1.0000
5.750 1.1455 0.01171 0.00466 -0.0864 0.2485 1.0000
6.000 1.1696 0.01211 0.00491 -0.0860 0.2189 1.0000
6.250 1.1835 0.01370 0.00588 -0.0845 0.1266 1.0000
6.500 1.2041 0.01449 0.00651 -0.0837 0.1005 1.0000
6.750 1.2173 0.01612 0.00773 -0.0819 0.0195 1.0000
7.000 1.2406 0.01654 0.00823 -0.0813 0.0131 1.0000
7.250 1.2636 0.01698 0.00877 -0.0807 0.0113 1.0000
7.500 1.2851 0.01755 0.00945 -0.0800 0.0092 1.0000
7.750 1.3063 0.01813 0.01013 -0.0792 0.0080 1.0000
8.000 1.3271 0.01872 0.01081 -0.0783 0.0072 1.0000
8.250 1.3466 0.01939 0.01159 -0.0773 0.0065 1.0000
8.500 1.3636 0.02024 0.01254 -0.0760 0.0059 1.0000
8.750 1.3804 0.02105 0.01344 -0.0747 0.0053 1.0000
9.000 1.3957 0.02193 0.01442 -0.0731 0.0049 1.0000
9.250 1.4081 0.02289 0.01549 -0.0712 0.0046 1.0000
9.500 1.4171 0.02392 0.01662 -0.0688 0.0043 1.0000
9.750 1.4243 0.02510 0.01789 -0.0664 0.0041 1.0000
10.000 1.4285 0.02654 0.01946 -0.0639 0.0039 1.0000
10.250 1.4275 0.02849 0.02154 -0.0614 0.0038 1.0000
10.500 1.4232 0.03089 0.02408 -0.0591 0.0037 1.0000
10.750 1.4219 0.03324 0.02657 -0.0575 0.0036 1.0000
11.000 1.4195 0.03588 0.02935 -0.0562 0.0036 1.0000
11.250 1.4167 0.03877 0.03238 -0.0554 0.0034 1.0000
11.500 1.4127 0.04203 0.03577 -0.0549 0.0033 1.0000
11.750 1.4084 0.04559 0.03947 -0.0550 0.0031 1.0000
12.000 1.4036 0.04944 0.04344 -0.0554 0.0030 1.0000
12.250 1.3978 0.05355 0.04767 -0.0561 0.0029 1.0000
12.500 1.3912 0.05784 0.05209 -0.0568 0.0028 1.0000
12.750 1.3833 0.06230 0.05666 -0.0575 0.0027 1.0000
13.000 1.3750 0.06680 0.06127 -0.0583 0.0027 1.0000
13.250 1.3681 0.07120 0.06577 -0.0591 0.0026 1.0000
13.500 1.3608 0.07562 0.07028 -0.0598 0.0026 1.0000
13.750 1.3546 0.07992 0.07467 -0.0606 0.0026 1.0000
14.000 1.3492 0.08414 0.07898 -0.0614 0.0025 1.0000
14.250 1.3444 0.08829 0.08321 -0.0622 0.0025 1.0000
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Polar data table (+)
Polar graphs
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