GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 15 AIRFOIL (goe15-il) Reynolds number: 500,000 Max Cl/Cd: 126.37 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe15-il-500000.txt Download as CSV file: xf-goe15-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 15 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0666 0.10921 0.10711 -0.0530 0.9740 0.0210
-10.750 -0.0524 0.10558 0.10347 -0.0560 0.9686 0.0215
-10.500 -0.1587 0.11591 0.11372 -0.0414 0.9936 0.0206
-10.250 -0.1418 0.11254 0.11034 -0.0448 0.9887 0.0210
-10.000 -0.1241 0.10907 0.10687 -0.0485 0.9830 0.0217
-9.750 -0.1091 0.10575 0.10355 -0.0516 0.9732 0.0225
-9.500 -0.0914 0.10250 0.10029 -0.0568 0.9629 0.0229
-9.000 -0.0440 0.09404 0.09178 -0.0678 0.9446 0.0232
-8.750 -0.0089 0.08967 0.08735 -0.0754 0.9355 0.0235
-8.250 0.0644 0.08153 0.07901 -0.0924 0.9015 0.0251
-8.000 0.0840 0.07878 0.07612 -0.0964 0.8736 0.0259
-7.750 0.0886 0.07720 0.07442 -0.0978 0.8428 0.0262
-7.500 0.0853 0.07613 0.07324 -0.0978 0.8155 0.0263
-7.000 0.1002 0.07129 0.06823 -0.0983 0.7835 0.0264
-6.750 0.1099 0.06896 0.06585 -0.0981 0.7720 0.0266
-6.500 0.1200 0.06692 0.06375 -0.0986 0.7621 0.0268
-6.250 0.1313 0.06499 0.06175 -0.0993 0.7529 0.0271
-6.000 0.1440 0.06304 0.05977 -0.1003 0.7447 0.0276
-5.750 0.1579 0.06105 0.05772 -0.1015 0.7369 0.0283
-5.500 0.1735 0.05897 0.05557 -0.1030 0.7302 0.0291
-5.250 0.1894 0.04328 0.03997 -0.0970 0.7084 0.0297
-4.750 0.2348 0.05243 0.04881 -0.1101 0.7108 0.0299
-4.500 0.2489 0.05006 0.04643 -0.1098 0.7042 0.0301
-4.250 0.2666 0.04814 0.04443 -0.1102 0.6974 0.0304
-4.000 0.2868 0.04627 0.04254 -0.1111 0.6905 0.0309
-3.750 0.3083 0.04443 0.04063 -0.1120 0.6831 0.0315
-3.500 0.3312 0.04259 0.03871 -0.1130 0.6762 0.0323
-3.250 0.3651 0.04119 0.03715 -0.1153 0.6682 0.0334
-3.000 0.3968 0.03973 0.03545 -0.1169 0.6606 0.0335
-2.750 0.4115 0.03710 0.03287 -0.1163 0.6515 0.0337
-2.500 0.4297 0.03525 0.03096 -0.1160 0.6418 0.0340
-2.250 0.4511 0.03371 0.02937 -0.1159 0.6294 0.0344
-2.000 0.4740 0.03230 0.02785 -0.1159 0.6151 0.0349
-1.750 0.4975 0.03097 0.02639 -0.1157 0.5982 0.0357
-1.500 0.5264 0.03007 0.02526 -0.1155 0.5776 0.0373
-0.500 0.5925 0.01130 0.00596 -0.1068 0.4808 0.0388
-0.250 0.6162 0.01075 0.00526 -0.1065 0.4720 0.0397
0.000 0.6430 0.01030 0.00465 -0.1061 0.4645 0.0414
0.250 0.6940 0.02374 0.01752 -0.1100 0.4646 0.0420
1.000 0.7414 0.00832 0.00213 -0.1044 0.4414 0.0438
1.250 0.7667 0.00804 0.00174 -0.1039 0.4371 0.0457
1.500 0.7962 0.00795 0.00139 -0.1029 0.4331 0.0473
1.750 0.8189 0.00735 0.00077 -0.1026 0.4288 0.0479
2.000 0.8424 0.00707 0.00040 -0.1022 0.4247 0.0487
2.250 0.8669 0.00686 0.00010 -0.1016 0.4206 0.0503
2.500 0.9118 0.01797 0.01075 -0.1036 0.4199 0.0528
2.750 0.9350 0.01678 0.00958 -0.1032 0.4167 0.0538
3.000 0.9589 0.01634 0.00912 -0.1026 0.4128 0.0550
3.250 0.9832 0.01612 0.00880 -0.1019 0.4082 0.0575
3.500 1.0082 0.01597 0.00847 -0.1009 0.4036 0.0606
3.750 1.0323 0.01554 0.00810 -0.1004 0.3999 0.0623
4.000 1.0583 0.01606 0.00848 -0.0995 0.3960 0.0675
4.250 1.0810 0.01515 0.00760 -0.0989 0.3920 0.0702
6.000 1.2473 0.01460 0.00688 -0.0931 0.3677 0.0770
6.250 1.2692 0.01435 0.00673 -0.0920 0.3645 0.0727
6.500 1.2910 0.01432 0.00673 -0.0908 0.3608 0.0727
6.750 1.3121 0.01436 0.00677 -0.0896 0.3570 0.0731
7.000 1.3331 0.01454 0.00690 -0.0884 0.3530 0.0732
7.250 1.3544 0.01454 0.00700 -0.0872 0.3499 0.0740
7.500 1.3752 0.01461 0.00712 -0.0860 0.3461 0.0755
7.750 1.3941 0.01469 0.00723 -0.0844 0.3423 0.0784
8.000 1.4120 0.01486 0.00739 -0.0827 0.3384 0.0810
8.250 1.4307 0.01504 0.00761 -0.0811 0.3346 0.0839
8.500 1.4494 0.01517 0.00780 -0.0795 0.3304 0.0883
8.750 1.4672 0.01535 0.00801 -0.0778 0.3257 0.0995
9.000 1.5214 0.01478 0.00862 -0.0844 0.3168 1.0000
9.250 1.5384 0.01500 0.00886 -0.0827 0.3103 1.0000
9.500 1.5526 0.01537 0.00918 -0.0805 0.3043 1.0000
9.750 1.5707 0.01560 0.00947 -0.0790 0.2970 1.0000
10.000 1.5839 0.01603 0.00987 -0.0768 0.2890 1.0000
10.250 1.6006 0.01637 0.01025 -0.0753 0.2806 1.0000
10.500 1.6131 0.01690 0.01075 -0.0732 0.2722 1.0000
10.750 1.6269 0.01741 0.01126 -0.0713 0.2618 1.0000
11.000 1.6388 0.01804 0.01189 -0.0693 0.2512 1.0000
11.250 1.6484 0.01882 0.01264 -0.0671 0.2403 1.0000
11.500 1.6570 0.01971 0.01348 -0.0650 0.2288 1.0000
11.750 1.6670 0.02057 0.01434 -0.0630 0.2184 1.0000
12.000 1.6741 0.02164 0.01539 -0.0609 0.2077 1.0000
12.500 1.6881 0.02396 0.01771 -0.0572 0.1904 1.0000
12.750 1.6921 0.02542 0.01915 -0.0552 0.1829 1.0000
13.000 1.6997 0.02669 0.02045 -0.0537 0.1755 1.0000
13.250 1.7017 0.02844 0.02219 -0.0520 0.1686 1.0000
13.500 1.7095 0.02980 0.02362 -0.0508 0.1625 1.0000
13.750 1.7105 0.03178 0.02561 -0.0494 0.1560 1.0000
14.000 1.7155 0.03348 0.02736 -0.0483 0.1488 1.0000
14.250 1.7146 0.03576 0.02964 -0.0471 0.1419 1.0000
14.500 1.7158 0.03791 0.03182 -0.0460 0.1326 1.0000
14.750 1.7122 0.04058 0.03450 -0.0450 0.1233 1.0000
15.000 1.7046 0.04376 0.03765 -0.0440 0.1118 1.0000
15.250 1.6870 0.04810 0.04193 -0.0431 0.0949 1.0000
15.500 1.6680 0.05285 0.04664 -0.0425 0.0818 1.0000
15.750 1.6481 0.05791 0.05170 -0.0422 0.0709 1.0000
16.000 1.6291 0.06313 0.05695 -0.0423 0.0614 1.0000
16.250 1.6058 0.06908 0.06292 -0.0427 0.0509 1.0000
16.500 1.5796 0.07566 0.06950 -0.0435 0.0392 1.0000
16.750 1.5552 0.08214 0.07600 -0.0445 0.0296 1.0000
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Polar data table (+)
Polar graphs
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