GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 527 AIRFOIL (goe527-il) Reynolds number: 100,000 Max Cl/Cd: 46.95 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe527-il-100000-n5.txt Download as CSV file: xf-goe527-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 527 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1027 0.09653 0.09133 -0.0840 0.9280 0.0571
-10.250 -0.0908 0.09178 0.08653 -0.0890 0.9189 0.0578
-10.000 -0.0801 0.08680 0.08151 -0.0941 0.9088 0.0578
-9.750 -0.0725 0.08169 0.07635 -0.0990 0.8973 0.0575
-9.500 -0.0667 0.07606 0.07066 -0.1046 0.8862 0.0573
-9.250 -0.0697 0.07042 0.06497 -0.1093 0.8718 0.0573
-9.000 -0.0843 0.06346 0.05798 -0.1151 0.8565 0.0579
-8.750 -0.1482 0.05130 0.04554 -0.1233 0.8376 0.0573
-8.500 -0.1751 0.04551 0.03934 -0.1238 0.8247 0.0577
-8.250 -0.1856 0.04123 0.03459 -0.1229 0.8138 0.0584
-8.000 -0.1885 0.03776 0.03064 -0.1213 0.8032 0.0591
-7.750 -0.1832 0.03452 0.02680 -0.1199 0.7945 0.0600
-7.500 -0.1695 0.03281 0.02482 -0.1185 0.7851 0.0608
-7.250 -0.1480 0.03189 0.02377 -0.1179 0.7768 0.0619
-7.000 -0.1284 0.03091 0.02263 -0.1169 0.7683 0.0634
-6.750 -0.1093 0.02965 0.02107 -0.1159 0.7600 0.0653
-6.500 -0.0891 0.02806 0.01901 -0.1149 0.7530 0.0673
-6.250 -0.0680 0.02730 0.01820 -0.1139 0.7442 0.0686
-6.000 -0.0427 0.02652 0.01727 -0.1135 0.7375 0.0703
-5.750 -0.0214 0.02579 0.01638 -0.1124 0.7290 0.0726
-5.500 0.0026 0.02492 0.01522 -0.1116 0.7217 0.0759
-5.250 0.0276 0.02447 0.01475 -0.1112 0.7152 0.0785
-5.000 0.0504 0.02394 0.01412 -0.1102 0.7072 0.0820
-4.750 0.0764 0.02327 0.01325 -0.1097 0.7010 0.0858
-4.500 0.0998 0.02289 0.01287 -0.1089 0.6937 0.0897
-4.250 0.1244 0.02250 0.01227 -0.1082 0.6865 0.0955
-4.000 0.1507 0.02200 0.01180 -0.1079 0.6811 0.1005
-3.750 0.1736 0.02174 0.01143 -0.1069 0.6740 0.1070
-3.500 0.1976 0.02134 0.01108 -0.1062 0.6675 0.1131
-3.250 0.2249 0.02104 0.01062 -0.1059 0.6624 0.1211
-3.000 0.2463 0.02075 0.01043 -0.1048 0.6554 0.1281
-2.500 0.2969 0.02023 0.00985 -0.1037 0.6446 0.1452
-2.250 0.3197 0.02008 0.00971 -0.1027 0.6386 0.1541
-2.000 0.3431 0.01991 0.00957 -0.1018 0.6325 0.1648
-1.750 0.3691 0.01969 0.00936 -0.1013 0.6277 0.1784
-1.500 0.3938 0.01953 0.00924 -0.1007 0.6228 0.1991
-1.250 0.4158 0.01938 0.00926 -0.0997 0.6169 0.2327
-1.000 0.4402 0.01911 0.00920 -0.0991 0.6119 0.2963
-0.750 0.4666 0.01877 0.00914 -0.0988 0.6078 0.3926
-0.500 0.4879 0.01863 0.00932 -0.0976 0.6024 0.4895
-0.250 0.5090 0.01847 0.00946 -0.0961 0.5972 0.5842
0.000 0.5335 0.01816 0.00954 -0.0949 0.5927 0.7078
0.250 0.6114 0.01799 0.00962 -0.1036 0.5882 0.9283
0.500 0.6737 0.01824 0.00979 -0.1107 0.5818 0.9971
0.750 0.6972 0.01843 0.00985 -0.1100 0.5769 1.0000
1.000 0.7207 0.01858 0.00983 -0.1092 0.5729 1.0000
1.250 0.7404 0.01882 0.00998 -0.1077 0.5682 1.0000
1.500 0.7578 0.01912 0.01023 -0.1059 0.5629 1.0000
1.750 0.7793 0.01932 0.01033 -0.1047 0.5582 1.0000
2.000 0.8046 0.01947 0.01032 -0.1042 0.5541 1.0000
2.250 0.8213 0.01979 0.01062 -0.1022 0.5487 1.0000
2.500 0.8395 0.02003 0.01081 -0.1005 0.5423 1.0000
2.750 0.8646 0.02011 0.01074 -0.0998 0.5367 1.0000
3.000 0.8809 0.02039 0.01100 -0.0978 0.5299 1.0000
3.250 0.8997 0.02061 0.01117 -0.0961 0.5233 1.0000
3.500 0.9252 0.02072 0.01116 -0.0956 0.5183 1.0000
3.750 0.9413 0.02108 0.01152 -0.0936 0.5126 1.0000
4.000 0.9589 0.02139 0.01183 -0.0919 0.5068 1.0000
4.250 0.9824 0.02158 0.01194 -0.0911 0.5019 1.0000
4.500 1.0037 0.02185 0.01216 -0.0900 0.4971 1.0000
4.750 1.0168 0.02227 0.01264 -0.0876 0.4908 1.0000
5.000 1.0375 0.02252 0.01285 -0.0864 0.4854 1.0000
5.250 1.0637 0.02267 0.01290 -0.0861 0.4811 1.0000
5.500 1.0717 0.02323 0.01357 -0.0830 0.4746 1.0000
5.750 1.0889 0.02356 0.01390 -0.0813 0.4690 1.0000
6.000 1.1137 0.02372 0.01399 -0.0807 0.4644 1.0000
6.250 1.1206 0.02428 0.01463 -0.0775 0.4579 1.0000
6.500 1.1327 0.02466 0.01503 -0.0750 0.4516 1.0000
6.750 1.1566 0.02479 0.01509 -0.0743 0.4465 1.0000
7.000 1.1562 0.02552 0.01591 -0.0701 0.4394 1.0000
7.250 1.1690 0.02594 0.01635 -0.0679 0.4331 1.0000
7.500 1.1870 0.02624 0.01661 -0.0665 0.4276 1.0000
7.750 1.1882 0.02712 0.01759 -0.0630 0.4202 1.0000
8.000 1.2043 0.02750 0.01796 -0.0615 0.4143 1.0000
8.250 1.2113 0.02829 0.01880 -0.0590 0.4075 1.0000
8.500 1.2183 0.02910 0.01965 -0.0566 0.4003 1.0000
8.750 1.2350 0.02951 0.02002 -0.0553 0.3941 1.0000
9.000 1.2333 0.03083 0.02143 -0.0523 0.3857 1.0000
9.250 1.2517 0.03116 0.02170 -0.0513 0.3793 1.0000
9.500 1.2472 0.03280 0.02346 -0.0485 0.3706 1.0000
9.750 1.2622 0.03337 0.02397 -0.0472 0.3639 1.0000
10.000 1.2612 0.03503 0.02571 -0.0450 0.3559 1.0000
10.250 1.2721 0.03593 0.02659 -0.0437 0.3490 1.0000
10.500 1.2762 0.03740 0.02812 -0.0421 0.3419 1.0000
10.750 1.2812 0.03882 0.02956 -0.0407 0.3347 1.0000
11.000 1.2915 0.03990 0.03062 -0.0395 0.3283 1.0000
11.250 1.2899 0.04196 0.03276 -0.0380 0.3207 1.0000
11.500 1.3076 0.04244 0.03316 -0.0372 0.3149 1.0000
11.750 1.3000 0.04519 0.03605 -0.0358 0.3077 1.0000
12.000 1.3088 0.04653 0.03739 -0.0349 0.3020 1.0000
12.250 1.3190 0.04779 0.03865 -0.0341 0.2969 1.0000
12.500 1.3160 0.05038 0.04136 -0.0332 0.2910 1.0000
12.750 1.3257 0.05174 0.04274 -0.0325 0.2862 1.0000
13.000 1.3416 0.05252 0.04350 -0.0319 0.2821 1.0000
13.250 1.3331 0.05585 0.04699 -0.0312 0.2766 1.0000
13.500 1.3374 0.05788 0.04909 -0.0306 0.2719 1.0000
13.750 1.3561 0.05837 0.04955 -0.0301 0.2681 1.0000
14.000 1.3526 0.06134 0.05265 -0.0297 0.2634 1.0000
14.250 1.3457 0.06477 0.05622 -0.0295 0.2583 1.0000
14.500 1.3545 0.06640 0.05788 -0.0291 0.2541 1.0000
14.750 1.3800 0.06607 0.05750 -0.0286 0.2508 1.0000
15.000 1.3535 0.07203 0.06370 -0.0289 0.2454 1.0000
15.250 1.3468 0.07569 0.06749 -0.0290 0.2404 1.0000
15.500 1.3620 0.07656 0.06837 -0.0287 0.2367 1.0000
15.750 1.3751 0.07770 0.06953 -0.0284 0.2330 1.0000
16.000 1.3299 0.08674 0.07884 -0.0300 0.2262 1.0000
16.250 1.3370 0.08870 0.08086 -0.0301 0.2219 1.0000
16.500 1.3650 0.08775 0.07987 -0.0294 0.2190 1.0000
16.750 1.2859 0.10244 0.09489 -0.0333 0.2099 1.0000
17.000 1.2943 0.10431 0.09681 -0.0335 0.2062 1.0000
17.250 1.3227 0.10310 0.09561 -0.0327 0.2040 1.0000
17.750 1.1286 0.14362 0.13648 -0.0481 0.1773 1.0000
18.000 1.1414 0.14480 0.13772 -0.0484 0.1757 1.0000
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