GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 14 AIRFOIL (goe14-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.5 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe14-il-1000000.txt Download as CSV file: xf-goe14-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2228 0.11949 0.11774 -0.0219 0.9205 0.0176
-10.250 -0.2164 0.11696 0.11512 -0.0224 0.8994 0.0180
-10.000 -0.2092 0.11423 0.11231 -0.0233 0.8817 0.0185
-9.750 -0.2017 0.11127 0.10929 -0.0248 0.8664 0.0188
-9.500 -0.1951 0.10836 0.10633 -0.0268 0.8533 0.0189
-9.250 -0.1889 0.10554 0.10345 -0.0289 0.8412 0.0190
-8.750 -0.1733 0.09936 0.09719 -0.0312 0.8200 0.0191
-8.500 -0.1636 0.09671 0.09450 -0.0318 0.8100 0.0191
-8.250 -0.1537 0.09424 0.09201 -0.0327 0.8011 0.0192
-8.000 -0.1436 0.09186 0.08958 -0.0339 0.7917 0.0194
-7.750 -0.1333 0.08947 0.08717 -0.0352 0.7830 0.0195
-7.500 -0.1227 0.08706 0.08474 -0.0367 0.7739 0.0197
-7.250 -0.1117 0.08461 0.08226 -0.0384 0.7656 0.0199
-7.000 -0.1006 0.08218 0.07981 -0.0405 0.7569 0.0202
-6.750 -0.0858 0.07946 0.07705 -0.0435 0.7486 0.0205
-6.500 -0.0692 0.07658 0.07415 -0.0470 0.7398 0.0211
-6.250 -0.0457 0.07285 0.07034 -0.0542 0.7312 0.0219
-6.000 -0.0193 0.06905 0.06650 -0.0621 0.7227 0.0219
-5.500 0.0194 0.06262 0.05998 -0.0675 0.7040 0.0221
-5.250 0.0390 0.06018 0.05748 -0.0694 0.6931 0.0222
-5.000 0.0612 0.05781 0.05505 -0.0718 0.6809 0.0224
-4.750 0.0850 0.05547 0.05264 -0.0745 0.6681 0.0226
-4.500 0.1102 0.05313 0.05022 -0.0774 0.6530 0.0228
-4.250 0.1363 0.05078 0.04777 -0.0803 0.6353 0.0232
-4.000 0.1636 0.04843 0.04530 -0.0831 0.6150 0.0239
-3.750 0.2078 0.04481 0.04142 -0.0898 0.5940 0.0251
-3.500 0.2349 0.04169 0.03814 -0.0923 0.5723 0.0253
-2.750 0.3086 0.03666 0.03278 -0.0955 0.5193 0.0259
-2.500 0.3364 0.03506 0.03107 -0.0968 0.5073 0.0263
-2.250 0.3650 0.03343 0.02930 -0.0980 0.4957 0.0269
-2.000 0.4053 0.03107 0.02669 -0.1000 0.4867 0.0285
-1.750 0.4324 0.02872 0.02420 -0.1011 0.4775 0.0288
-1.500 0.4581 0.02745 0.02288 -0.1016 0.4695 0.0290
-1.250 0.4848 0.02638 0.02171 -0.1021 0.4608 0.0293
-1.000 0.5127 0.02529 0.02055 -0.1026 0.4537 0.0300
-0.750 0.5485 0.02307 0.01803 -0.1029 0.4465 0.0324
-0.500 0.5745 0.02204 0.01693 -0.1033 0.4390 0.0327
-0.250 0.6015 0.02125 0.01608 -0.1036 0.4315 0.0331
0.000 0.6290 0.02051 0.01524 -0.1037 0.4238 0.0338
0.500 0.6935 0.01076 0.00417 -0.1033 0.4151 0.0318
0.750 0.7210 0.01046 0.00375 -0.1031 0.4082 0.0322
1.000 0.7486 0.01008 0.00331 -0.1030 0.4024 0.0332
1.250 0.7765 0.01001 0.00323 -0.1029 0.3962 0.0343
1.500 0.8039 0.00995 0.00310 -0.1027 0.3893 0.0353
1.750 0.8319 0.00986 0.00298 -0.1026 0.3841 0.0362
2.000 0.8596 0.00978 0.00289 -0.1025 0.3779 0.0378
2.250 0.8870 0.00982 0.00289 -0.1023 0.3708 0.0396
2.500 0.9150 0.00980 0.00288 -0.1022 0.3656 0.0423
2.750 0.9426 0.00987 0.00295 -0.1021 0.3585 0.0466
3.000 0.9701 0.01007 0.00315 -0.1019 0.3515 0.0519
3.250 0.9979 0.01028 0.00335 -0.1018 0.3444 0.0566
3.500 1.0250 0.01059 0.00363 -0.1016 0.3364 0.0595
3.750 1.0527 0.01070 0.00374 -0.1015 0.3311 0.0627
4.000 1.0799 0.01092 0.00395 -0.1013 0.3248 0.0650
4.250 1.1067 0.01108 0.00405 -0.1011 0.3186 0.0686
4.500 1.1340 0.01115 0.00415 -0.1011 0.3134 0.0708
4.750 1.1607 0.01130 0.00428 -0.1009 0.3073 0.0739
5.000 1.1872 0.01140 0.00436 -0.1007 0.3015 0.0776
5.250 1.2141 0.01147 0.00444 -0.1006 0.2961 0.0798
5.500 1.2402 0.01158 0.00452 -0.1003 0.2895 0.0812
5.750 1.2667 0.01169 0.00462 -0.1001 0.2842 0.0825
6.000 1.2932 0.01179 0.00472 -0.0999 0.2792 0.0832
6.250 1.3191 0.01190 0.00480 -0.0997 0.2736 0.0841
6.500 1.3451 0.01201 0.00492 -0.0995 0.2687 0.0858
6.750 1.3714 0.01212 0.00505 -0.0993 0.2641 0.0870
7.000 1.3970 0.01230 0.00522 -0.0991 0.2592 0.0881
7.250 1.4221 0.01252 0.00542 -0.0987 0.2541 0.0894
7.500 1.4482 0.01265 0.00558 -0.0986 0.2512 0.0908
7.750 1.4737 0.01282 0.00577 -0.0983 0.2477 0.0922
8.000 1.4987 0.01302 0.00597 -0.0980 0.2438 0.0944
8.250 1.5228 0.01329 0.00623 -0.0975 0.2394 0.0965
8.500 1.5481 0.01345 0.00644 -0.0972 0.2369 0.0990
8.750 1.5731 0.01364 0.00666 -0.0969 0.2341 0.1015
9.000 1.5974 0.01386 0.00689 -0.0965 0.2305 0.1070
9.250 1.6203 0.01418 0.00720 -0.0960 0.2254 0.1150
9.500 1.6427 0.01341 0.00768 -0.0955 0.2219 1.0000
9.750 1.6668 0.01364 0.00793 -0.0951 0.2187 1.0000
10.000 1.6897 0.01395 0.00822 -0.0945 0.2144 1.0000
10.250 1.7108 0.01437 0.00861 -0.0937 0.2088 1.0000
10.500 1.7341 0.01461 0.00888 -0.0932 0.2049 1.0000
10.750 1.7555 0.01496 0.00923 -0.0925 0.1991 1.0000
11.000 1.7751 0.01541 0.00966 -0.0915 0.1929 1.0000
11.250 1.7957 0.01574 0.01000 -0.0906 0.1875 1.0000
11.500 1.8112 0.01629 0.01051 -0.0889 0.1798 1.0000
11.750 1.8283 0.01674 0.01097 -0.0876 0.1722 1.0000
12.000 1.8415 0.01743 0.01161 -0.0858 0.1624 1.0000
12.250 1.8523 0.01828 0.01240 -0.0838 0.1511 1.0000
12.750 1.8720 0.02020 0.01426 -0.0800 0.1335 1.0000
13.000 1.8799 0.02136 0.01540 -0.0781 0.1268 1.0000
13.250 1.8906 0.02237 0.01644 -0.0766 0.1225 1.0000
13.500 1.8984 0.02364 0.01772 -0.0750 0.1181 1.0000
13.750 1.9071 0.02490 0.01901 -0.0737 0.1145 1.0000
14.000 1.9176 0.02605 0.02021 -0.0725 0.1121 1.0000
14.250 1.9256 0.02745 0.02165 -0.0713 0.1092 1.0000
14.500 1.9306 0.02914 0.02338 -0.0701 0.1061 1.0000
14.750 1.9357 0.03088 0.02516 -0.0689 0.1030 1.0000
15.000 1.9438 0.03239 0.02673 -0.0681 0.1004 1.0000
15.250 1.9472 0.03436 0.02875 -0.0671 0.0969 1.0000
15.500 1.9454 0.03689 0.03131 -0.0660 0.0929 1.0000
15.750 1.9488 0.03897 0.03345 -0.0653 0.0893 1.0000
16.000 1.9435 0.04200 0.03649 -0.0645 0.0835 1.0000
16.250 1.9362 0.04535 0.03987 -0.0638 0.0767 1.0000
16.500 1.9196 0.04994 0.04446 -0.0634 0.0682 1.0000
16.750 1.8993 0.05519 0.04974 -0.0633 0.0610 1.0000
17.000 1.8779 0.06084 0.05545 -0.0636 0.0556 1.0000
17.250 1.8557 0.06679 0.06146 -0.0642 0.0508 1.0000
17.500 1.8317 0.07311 0.06786 -0.0651 0.0463 1.0000
17.750 1.8062 0.07975 0.07459 -0.0661 0.0424 1.0000
18.000 1.7799 0.08661 0.08153 -0.0674 0.0381 1.0000
18.250 1.7523 0.09379 0.08878 -0.0689 0.0333 1.0000
18.500 1.7221 0.10149 0.09656 -0.0708 0.0281 1.0000
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