GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 500,000 Max Cl/Cd: 91.94 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe240-il-500000-n5.txt Download as CSV file: xf-goe240-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 240 (KOLLER) 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 -0.3295 0.10740 0.10512 -0.0247 1.0000 0.0073
-9.250 -0.3256 0.10387 0.10162 -0.0260 1.0000 0.0074
-9.000 -0.3241 0.09996 0.09773 -0.0273 1.0000 0.0077
-8.750 -0.3176 0.09808 0.09588 -0.0276 1.0000 0.0080
-8.500 -0.3098 0.09588 0.09370 -0.0286 0.9986 0.0083
-8.250 -0.2951 0.09245 0.09027 -0.0322 0.9930 0.0087
-8.000 -0.2812 0.08842 0.08625 -0.0364 0.9861 0.0088
-7.750 -0.2689 0.08446 0.08229 -0.0403 0.9775 0.0089
-7.500 -0.2564 0.08052 0.07835 -0.0445 0.9676 0.0091
-7.250 -0.2420 0.07631 0.07413 -0.0494 0.9566 0.0093
-7.000 -0.2272 0.07176 0.06956 -0.0546 0.9426 0.0097
-6.750 -0.2106 0.06514 0.06289 -0.0625 0.9218 0.0105
-6.500 -0.1922 0.06312 0.06078 -0.0646 0.8886 0.0109
-6.250 -0.1732 0.06065 0.05816 -0.0671 0.8562 0.0114
-6.000 -0.1507 0.05688 0.05422 -0.0716 0.8362 0.0119
-5.750 -0.1241 0.05208 0.04926 -0.0777 0.8230 0.0126
-5.500 -0.0895 0.04415 0.04108 -0.0871 0.8131 0.0143
-5.250 -0.0650 0.04298 0.03982 -0.0884 0.8042 0.0148
-5.000 -0.0369 0.04015 0.03684 -0.0914 0.7965 0.0157
-4.750 0.0043 0.02936 0.02550 -0.0995 0.7912 0.0187
-4.500 0.0302 0.02862 0.02469 -0.1002 0.7854 0.0192
-4.250 0.0571 0.02724 0.02316 -0.1010 0.7802 0.0198
-4.000 0.0859 0.02447 0.02014 -0.1022 0.7755 0.0209
-3.750 0.1165 0.01927 0.01437 -0.1035 0.7707 0.0232
-3.500 0.1450 0.01706 0.01170 -0.1038 0.7657 0.0240
-3.250 0.1725 0.01507 0.00931 -0.1041 0.7611 0.0250
-3.000 0.2001 0.01414 0.00823 -0.1043 0.7552 0.0257
-2.750 0.2277 0.01337 0.00727 -0.1043 0.7485 0.0262
-2.500 0.2555 0.01269 0.00644 -0.1043 0.7413 0.0267
-2.250 0.2833 0.01213 0.00572 -0.1043 0.7339 0.0271
-2.000 0.3112 0.01161 0.00509 -0.1042 0.7269 0.0275
-1.750 0.3389 0.01117 0.00452 -0.1041 0.7187 0.0278
-1.500 0.3667 0.01080 0.00407 -0.1040 0.7096 0.0283
-1.250 0.3943 0.01050 0.00368 -0.1039 0.7007 0.0289
-1.000 0.4222 0.01016 0.00328 -0.1038 0.6920 0.0291
-0.750 0.4499 0.00987 0.00293 -0.1037 0.6837 0.0292
-0.500 0.4776 0.00963 0.00264 -0.1036 0.6728 0.0294
-0.250 0.5050 0.00945 0.00239 -0.1034 0.6571 0.0297
0.000 0.5323 0.00931 0.00218 -0.1032 0.6367 0.0302
0.250 0.5591 0.00926 0.00201 -0.1029 0.6118 0.0308
0.500 0.5856 0.00928 0.00190 -0.1026 0.5821 0.0313
0.750 0.6116 0.00940 0.00185 -0.1022 0.5510 0.0318
1.000 0.6379 0.00952 0.00183 -0.1019 0.5260 0.0322
1.500 0.6916 0.00966 0.00181 -0.1016 0.4940 0.0344
1.750 0.7187 0.00972 0.00183 -0.1014 0.4797 0.0365
2.000 0.7450 0.00989 0.00189 -0.1012 0.4521 0.0379
2.250 0.7704 0.01016 0.00197 -0.1008 0.4082 0.0394
2.750 0.8209 0.01074 0.00229 -0.1001 0.3361 0.0785
3.000 0.8469 0.01096 0.00245 -0.0998 0.3166 0.0913
3.250 0.8729 0.01105 0.00266 -0.0997 0.3001 0.1784
3.750 0.9212 0.01002 0.00313 -0.0987 0.2680 1.0000
4.000 0.9469 0.01030 0.00332 -0.0984 0.2481 1.0000
4.250 0.9718 0.01066 0.00354 -0.0980 0.2222 1.0000
4.500 0.9961 0.01110 0.00381 -0.0975 0.1916 1.0000
4.750 1.0204 0.01152 0.00410 -0.0970 0.1691 1.0000
5.000 1.0452 0.01187 0.00438 -0.0966 0.1554 1.0000
5.250 1.0702 0.01219 0.00466 -0.0962 0.1446 1.0000
5.500 1.0945 0.01257 0.00496 -0.0957 0.1307 1.0000
5.750 1.1184 0.01299 0.00530 -0.0952 0.1151 1.0000
6.000 1.1424 0.01339 0.00563 -0.0947 0.1009 1.0000
6.250 1.1628 0.01418 0.00617 -0.0937 0.0604 1.0000
6.500 1.1859 0.01465 0.00662 -0.0931 0.0532 1.0000
6.750 1.2099 0.01499 0.00702 -0.0925 0.0485 1.0000
7.000 1.2331 0.01542 0.00746 -0.0919 0.0424 1.0000
7.250 1.2538 0.01609 0.00802 -0.0909 0.0195 1.0000
7.500 1.2751 0.01670 0.00862 -0.0900 0.0139 1.0000
7.750 1.2974 0.01717 0.00915 -0.0892 0.0125 1.0000
8.000 1.3189 0.01770 0.00978 -0.0882 0.0113 1.0000
8.250 1.3391 0.01834 0.01050 -0.0871 0.0100 1.0000
8.500 1.3576 0.01912 0.01138 -0.0858 0.0088 1.0000
8.750 1.3775 0.01970 0.01204 -0.0847 0.0083 1.0000
9.000 1.3961 0.02038 0.01280 -0.0834 0.0078 1.0000
9.250 1.4136 0.02112 0.01364 -0.0819 0.0074 1.0000
9.500 1.4297 0.02192 0.01452 -0.0803 0.0070 1.0000
9.750 1.4436 0.02280 0.01548 -0.0784 0.0066 1.0000
10.000 1.4524 0.02387 0.01663 -0.0757 0.0063 1.0000
10.250 1.4589 0.02510 0.01797 -0.0728 0.0060 1.0000
10.500 1.4699 0.02603 0.01899 -0.0707 0.0057 1.0000
10.750 1.4790 0.02712 0.02018 -0.0684 0.0054 1.0000
11.000 1.4857 0.02843 0.02162 -0.0661 0.0052 1.0000
11.250 1.4911 0.02990 0.02320 -0.0639 0.0050 1.0000
11.500 1.4954 0.03154 0.02494 -0.0618 0.0049 1.0000
11.750 1.4993 0.03332 0.02683 -0.0600 0.0047 1.0000
12.000 1.5020 0.03532 0.02894 -0.0584 0.0046 1.0000
12.250 1.5041 0.03749 0.03123 -0.0571 0.0045 1.0000
12.500 1.5051 0.03989 0.03373 -0.0560 0.0044 1.0000
12.750 1.5043 0.04256 0.03651 -0.0551 0.0043 1.0000
13.000 1.5016 0.04556 0.03963 -0.0543 0.0042 1.0000
13.250 1.4961 0.04896 0.04315 -0.0537 0.0041 1.0000
13.500 1.4882 0.05280 0.04713 -0.0533 0.0041 1.0000
13.750 1.4776 0.05708 0.05155 -0.0532 0.0040 1.0000
14.000 1.4712 0.06103 0.05564 -0.0533 0.0040 1.0000
14.250 1.4653 0.06512 0.05987 -0.0538 0.0039 1.0000
14.500 1.4588 0.06942 0.06431 -0.0545 0.0039 1.0000
14.750 1.4514 0.07398 0.06901 -0.0554 0.0038 1.0000
15.000 1.4436 0.07875 0.07392 -0.0565 0.0038 1.0000
15.250 1.4354 0.08370 0.07901 -0.0578 0.0038 1.0000
15.500 1.4267 0.08879 0.08424 -0.0592 0.0037 1.0000
15.750 1.4177 0.09406 0.08965 -0.0609 0.0037 1.0000
16.000 1.4085 0.09949 0.09522 -0.0627 0.0036 1.0000
16.250 1.3992 0.10503 0.10090 -0.0647 0.0036 1.0000
16.500 1.3895 0.11075 0.10674 -0.0669 0.0035 1.0000
16.750 1.3801 0.11655 0.11268 -0.0693 0.0035 1.0000
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