GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 415 AIRFOIL (goe415-il) Reynolds number: 500,000 Max Cl/Cd: 92.2 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe415-il-500000.txt Download as CSV file: xf-goe415-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 415 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4185 0.09168 0.08961 -0.0084 1.0000 0.0115
-7.750 -0.4134 0.08787 0.08583 -0.0110 1.0000 0.0115
-7.500 -0.4161 0.08244 0.08044 -0.0130 1.0000 0.0119
-7.250 -0.4078 0.07894 0.07696 -0.0152 1.0000 0.0121
-7.000 -0.3977 0.07529 0.07332 -0.0182 1.0000 0.0123
-6.750 -0.3859 0.07140 0.06944 -0.0220 1.0000 0.0126
-6.500 -0.3727 0.06730 0.06533 -0.0262 1.0000 0.0129
-6.250 -0.3587 0.06307 0.06109 -0.0302 1.0000 0.0132
-6.000 -0.3453 0.05885 0.05685 -0.0336 1.0000 0.0137
-5.750 -0.3338 0.05477 0.05271 -0.0359 1.0000 0.0142
-5.500 -0.3129 0.04981 0.04763 -0.0398 0.9984 0.0152
-5.250 -0.2616 0.04378 0.04119 -0.0474 0.9937 0.0167
-5.000 -0.2260 0.03921 0.03627 -0.0518 0.9876 0.0168
-4.750 -0.1986 0.03149 0.02833 -0.0568 0.9823 0.0181
-4.500 -0.1684 0.02930 0.02606 -0.0590 0.9734 0.0194
-4.250 -0.1356 0.02662 0.02312 -0.0608 0.9636 0.0209
-4.000 -0.1017 0.02461 0.02078 -0.0617 0.9521 0.0232
-3.750 -0.0690 0.02470 0.02054 -0.0614 0.9372 0.0246
-3.500 -0.0423 0.02293 0.01843 -0.0609 0.9204 0.0247
-3.250 -0.0199 0.01784 0.01285 -0.0605 0.9039 0.0264
-3.000 0.0047 0.01620 0.01104 -0.0597 0.8848 0.0277
-2.750 0.0319 0.01443 0.00893 -0.0582 0.8620 0.0224
-2.500 0.0578 0.01310 0.00733 -0.0571 0.8320 0.0222
-2.250 0.0832 0.01258 0.00652 -0.0559 0.7838 0.0235
-2.000 0.1079 0.01162 0.00521 -0.0547 0.7319 0.0233
-1.750 0.1337 0.01124 0.00456 -0.0538 0.6897 0.0243
-1.500 0.1593 0.01041 0.00353 -0.0532 0.6546 0.0259
-1.250 0.1853 0.00995 0.00294 -0.0527 0.6234 0.0301
-1.000 0.2121 0.00970 0.00252 -0.0523 0.5966 0.0332
-0.750 0.2392 0.00958 0.00225 -0.0520 0.5742 0.0358
-0.500 0.2664 0.00931 0.00183 -0.0518 0.5555 0.0441
-0.250 0.2938 0.00923 0.00163 -0.0515 0.5395 0.0550
0.000 0.3179 0.00803 0.00163 -0.0515 0.5264 0.4691
0.250 0.3547 0.00670 0.00165 -0.0532 0.5125 1.0000
0.500 0.3819 0.00682 0.00163 -0.0530 0.5002 1.0000
0.750 0.4091 0.00695 0.00163 -0.0528 0.4881 1.0000
1.000 0.4363 0.00707 0.00164 -0.0525 0.4758 1.0000
1.250 0.4636 0.00718 0.00166 -0.0524 0.4628 1.0000
1.500 0.4908 0.00730 0.00168 -0.0522 0.4491 1.0000
1.750 0.5180 0.00743 0.00172 -0.0520 0.4347 1.0000
2.000 0.5452 0.00757 0.00176 -0.0518 0.4195 1.0000
2.250 0.5723 0.00771 0.00181 -0.0516 0.4043 1.0000
2.500 0.5994 0.00786 0.00188 -0.0515 0.3902 1.0000
2.750 0.6265 0.00803 0.00198 -0.0513 0.3772 1.0000
3.000 0.6535 0.00819 0.00208 -0.0511 0.3647 1.0000
3.250 0.6806 0.00836 0.00220 -0.0510 0.3528 1.0000
3.500 0.7075 0.00854 0.00232 -0.0508 0.3410 1.0000
3.750 0.7345 0.00873 0.00248 -0.0506 0.3307 1.0000
4.000 0.7612 0.00895 0.00264 -0.0505 0.3212 1.0000
4.250 0.7882 0.00911 0.00279 -0.0503 0.3117 1.0000
4.500 0.8151 0.00931 0.00297 -0.0502 0.3029 1.0000
4.750 0.8417 0.00953 0.00317 -0.0500 0.2946 1.0000
5.000 0.8686 0.00970 0.00334 -0.0499 0.2837 1.0000
5.250 0.8953 0.00989 0.00353 -0.0497 0.2740 1.0000
5.500 0.9219 0.01011 0.00371 -0.0496 0.2610 1.0000
5.750 0.9483 0.01033 0.00393 -0.0494 0.2475 1.0000
6.000 0.9746 0.01057 0.00415 -0.0492 0.2338 1.0000
6.250 1.0004 0.01089 0.00439 -0.0490 0.2120 1.0000
6.500 1.0245 0.01147 0.00473 -0.0487 0.1631 1.0000
6.750 1.0436 0.01288 0.00564 -0.0479 0.0853 1.0000
7.000 1.0621 0.01443 0.00683 -0.0468 0.0194 1.0000
7.250 1.0861 0.01506 0.00758 -0.0462 0.0165 1.0000
7.500 1.1091 0.01584 0.00852 -0.0455 0.0143 1.0000
7.750 1.1303 0.01688 0.00974 -0.0446 0.0133 1.0000
8.000 1.1524 0.01768 0.01066 -0.0438 0.0128 1.0000
8.250 1.1728 0.01868 0.01180 -0.0428 0.0123 1.0000
8.500 1.1918 0.01980 0.01305 -0.0417 0.0118 1.0000
8.750 1.2100 0.02091 0.01426 -0.0406 0.0109 1.0000
9.000 1.2266 0.02214 0.01559 -0.0393 0.0103 1.0000
9.250 1.2408 0.02356 0.01712 -0.0378 0.0099 1.0000
9.500 1.2530 0.02512 0.01877 -0.0361 0.0097 1.0000
9.750 1.2627 0.02685 0.02060 -0.0341 0.0094 1.0000
10.000 1.2706 0.02876 0.02259 -0.0320 0.0092 1.0000
10.250 1.2778 0.03078 0.02468 -0.0298 0.0091 1.0000
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Polar data table (+)
Polar graphs
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