GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 500,000 Max Cl/Cd: 93.93 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe385-il-500000-n5.txt Download as CSV file: xf-goe385-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3846 0.10022 0.09803 -0.0193 1.0000 0.0084
-9.250 -0.3841 0.09548 0.09331 -0.0217 1.0000 0.0085
-9.000 -0.3839 0.09087 0.08873 -0.0242 1.0000 0.0087
-8.750 -0.3784 0.08790 0.08579 -0.0260 1.0000 0.0089
-8.500 -0.3714 0.08524 0.08315 -0.0278 0.9971 0.0091
-8.250 -0.3588 0.08178 0.07970 -0.0318 0.9770 0.0094
-8.000 -0.3505 0.07792 0.07583 -0.0360 0.9578 0.0098
-7.750 -0.3429 0.07317 0.07106 -0.0414 0.9376 0.0101
-7.500 -0.3349 0.06757 0.06539 -0.0475 0.9122 0.0104
-7.250 -0.3260 0.06081 0.05848 -0.0541 0.8814 0.0108
-7.000 -0.3175 0.04908 0.04641 -0.0637 0.8582 0.0116
-6.750 -0.2979 0.04663 0.04378 -0.0651 0.8411 0.0119
-6.500 -0.2768 0.04429 0.04126 -0.0664 0.8274 0.0124
-6.000 -0.2376 0.02951 0.02550 -0.0709 0.8072 0.0154
-5.750 -0.2127 0.02859 0.02444 -0.0711 0.7964 0.0158
-5.500 -0.1875 0.02756 0.02326 -0.0713 0.7857 0.0166
-5.250 -0.1651 0.02019 0.01492 -0.0710 0.7767 0.0199
-5.000 -0.1385 0.01985 0.01450 -0.0711 0.7647 0.0204
-4.750 -0.1117 0.01960 0.01417 -0.0712 0.7514 0.0210
-4.500 -0.0848 0.01913 0.01355 -0.0712 0.7366 0.0217
-4.250 -0.0579 0.01804 0.01222 -0.0712 0.7203 0.0227
-3.750 -0.0032 0.01626 0.00989 -0.0709 0.6855 0.0249
-3.500 0.0243 0.01562 0.00899 -0.0708 0.6685 0.0255
-3.250 0.0519 0.01520 0.00835 -0.0707 0.6519 0.0258
-3.000 0.0787 0.01384 0.00674 -0.0706 0.6375 0.0269
-2.750 0.1062 0.01329 0.00606 -0.0706 0.6256 0.0276
-2.500 0.1340 0.01282 0.00550 -0.0707 0.6166 0.0281
-2.250 0.1620 0.01242 0.00501 -0.0707 0.6099 0.0287
-2.000 0.1900 0.01204 0.00457 -0.0707 0.6029 0.0291
-1.750 0.2180 0.01171 0.00417 -0.0707 0.5966 0.0296
-1.500 0.2462 0.01139 0.00381 -0.0708 0.5898 0.0300
-1.000 0.3025 0.01092 0.00325 -0.0709 0.5766 0.0314
-0.750 0.3306 0.01070 0.00299 -0.0710 0.5698 0.0319
-0.500 0.3589 0.01049 0.00274 -0.0711 0.5634 0.0323
-0.250 0.3872 0.01032 0.00254 -0.0712 0.5562 0.0328
0.000 0.4156 0.01018 0.00237 -0.0713 0.5490 0.0334
0.250 0.4439 0.01009 0.00224 -0.0714 0.5399 0.0341
0.500 0.4723 0.01001 0.00213 -0.0715 0.5296 0.0347
0.750 0.5005 0.00998 0.00206 -0.0716 0.5176 0.0351
1.000 0.5287 0.00993 0.00194 -0.0717 0.5051 0.0364
1.250 0.5568 0.00993 0.00188 -0.0718 0.4927 0.0382
1.500 0.5848 0.00995 0.00186 -0.0718 0.4783 0.0416
1.750 0.6127 0.01001 0.00187 -0.0719 0.4617 0.0454
2.000 0.6385 0.00884 0.00202 -0.0725 0.4440 0.6029
2.250 0.6634 0.00805 0.00210 -0.0715 0.4250 1.0000
2.750 0.7175 0.00849 0.00229 -0.0714 0.3865 1.0000
3.000 0.7446 0.00871 0.00241 -0.0714 0.3693 1.0000
3.250 0.7717 0.00893 0.00254 -0.0714 0.3551 1.0000
3.500 0.7988 0.00914 0.00268 -0.0714 0.3431 1.0000
3.750 0.8255 0.00939 0.00284 -0.0713 0.3283 1.0000
4.000 0.8522 0.00964 0.00301 -0.0713 0.3137 1.0000
4.500 0.9061 0.01006 0.00336 -0.0712 0.2942 1.0000
4.750 0.9328 0.01029 0.00355 -0.0712 0.2867 1.0000
5.000 0.9599 0.01046 0.00373 -0.0712 0.2805 1.0000
5.250 0.9866 0.01068 0.00394 -0.0711 0.2739 1.0000
5.500 1.0134 0.01087 0.00414 -0.0711 0.2683 1.0000
5.750 1.0400 0.01108 0.00435 -0.0711 0.2616 1.0000
6.000 1.0661 0.01135 0.00459 -0.0710 0.2508 1.0000
6.250 1.0913 0.01169 0.00487 -0.0708 0.2326 1.0000
6.500 1.1163 0.01205 0.00516 -0.0705 0.2155 1.0000
6.750 1.1408 0.01246 0.00548 -0.0702 0.1965 1.0000
7.000 1.1635 0.01305 0.00591 -0.0697 0.1609 1.0000
7.250 1.1831 0.01396 0.00657 -0.0689 0.1211 1.0000
7.500 1.2054 0.01455 0.00709 -0.0683 0.1062 1.0000
7.750 1.2275 0.01513 0.00761 -0.0677 0.0875 1.0000
8.000 1.2453 0.01612 0.00840 -0.0665 0.0529 1.0000
8.250 1.2660 0.01678 0.00904 -0.0657 0.0409 1.0000
8.500 1.2820 0.01784 0.00996 -0.0642 0.0168 1.0000
8.750 1.3025 0.01845 0.01061 -0.0633 0.0140 1.0000
9.000 1.3215 0.01914 0.01137 -0.0622 0.0123 1.0000
9.250 1.3398 0.01984 0.01217 -0.0611 0.0110 1.0000
9.500 1.3584 0.02047 0.01287 -0.0599 0.0102 1.0000
9.750 1.3752 0.02118 0.01366 -0.0586 0.0094 1.0000
10.000 1.3899 0.02197 0.01453 -0.0570 0.0088 1.0000
10.250 1.3995 0.02291 0.01555 -0.0545 0.0083 1.0000
10.500 1.4063 0.02408 0.01682 -0.0519 0.0079 1.0000
10.750 1.4165 0.02509 0.01792 -0.0500 0.0077 1.0000
11.000 1.4253 0.02624 0.01919 -0.0482 0.0074 1.0000
11.250 1.4331 0.02755 0.02060 -0.0464 0.0071 1.0000
11.500 1.4400 0.02902 0.02216 -0.0449 0.0068 1.0000
11.750 1.4462 0.03065 0.02388 -0.0436 0.0065 1.0000
12.000 1.4516 0.03246 0.02578 -0.0425 0.0062 1.0000
12.250 1.4553 0.03453 0.02795 -0.0416 0.0060 1.0000
12.500 1.4556 0.03706 0.03058 -0.0409 0.0058 1.0000
12.750 1.4518 0.04017 0.03381 -0.0403 0.0056 1.0000
13.000 1.4475 0.04352 0.03728 -0.0401 0.0055 1.0000
13.250 1.4463 0.04665 0.04056 -0.0401 0.0054 1.0000
13.500 1.4437 0.05005 0.04408 -0.0404 0.0054 1.0000
13.750 1.4393 0.05372 0.04787 -0.0407 0.0053 1.0000
14.000 1.4337 0.05760 0.05188 -0.0411 0.0052 1.0000
14.250 1.4266 0.06171 0.05611 -0.0417 0.0051 1.0000
14.500 1.4190 0.06602 0.06054 -0.0424 0.0050 1.0000
14.750 1.4114 0.07048 0.06513 -0.0433 0.0050 1.0000
15.000 1.4033 0.07510 0.06986 -0.0444 0.0049 1.0000
15.250 1.3949 0.07986 0.07474 -0.0456 0.0048 1.0000
15.500 1.3867 0.08473 0.07973 -0.0469 0.0047 1.0000
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Polar data table (+)
Polar graphs
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