GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 612 AIRFOIL (goe612-il) Reynolds number: 100,000 Max Cl/Cd: 49.26 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe612-il-100000-n5.txt Download as CSV file: xf-goe612-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 612 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3513 0.05384 0.04806 -0.1118 0.9375 0.0552
-9.250 -0.3749 0.04688 0.04058 -0.1164 0.9233 0.0552
-9.000 -0.3819 0.04258 0.03578 -0.1171 0.9116 0.0555
-8.750 -0.3727 0.04049 0.03352 -0.1163 0.9019 0.0559
-8.500 -0.3533 0.03861 0.03149 -0.1168 0.8954 0.0566
-8.250 -0.3377 0.03710 0.02982 -0.1162 0.8873 0.0575
-8.000 -0.3203 0.03549 0.02801 -0.1158 0.8797 0.0586
-7.750 -0.2968 0.03359 0.02580 -0.1165 0.8754 0.0599
-7.500 -0.2865 0.03220 0.02414 -0.1143 0.8649 0.0608
-7.250 -0.2626 0.03044 0.02202 -0.1144 0.8600 0.0620
-7.000 -0.2449 0.02917 0.02046 -0.1130 0.8521 0.0629
-6.750 -0.2214 0.02817 0.01943 -0.1126 0.8458 0.0639
-6.500 -0.1929 0.02721 0.01840 -0.1129 0.8419 0.0653
-6.250 -0.1740 0.02658 0.01768 -0.1116 0.8341 0.0671
-6.000 -0.1492 0.02576 0.01670 -0.1111 0.8283 0.0694
-5.750 -0.1201 0.02485 0.01565 -0.1113 0.8245 0.0718
-5.500 -0.1004 0.02438 0.01519 -0.1100 0.8169 0.0738
-5.250 -0.0754 0.02378 0.01453 -0.1095 0.8114 0.0764
-5.000 -0.0464 0.02308 0.01368 -0.1096 0.8077 0.0799
-4.750 -0.0243 0.02268 0.01332 -0.1086 0.8016 0.0835
-4.500 -0.0006 0.02228 0.01285 -0.1078 0.7955 0.0890
-4.250 0.0277 0.02175 0.01230 -0.1078 0.7914 0.0955
-4.000 0.0552 0.02127 0.01177 -0.1076 0.7873 0.1042
-3.750 0.0748 0.02105 0.01155 -0.1062 0.7804 0.1140
-3.500 0.1015 0.02062 0.01113 -0.1060 0.7759 0.1275
-3.250 0.1319 0.02017 0.01068 -0.1063 0.7725 0.1450
-3.000 0.1527 0.02004 0.01059 -0.1051 0.7663 0.1614
-2.750 0.1768 0.01984 0.01046 -0.1044 0.7610 0.1810
-2.500 0.2056 0.01956 0.01024 -0.1045 0.7571 0.2057
-2.250 0.2373 0.01926 0.01001 -0.1050 0.7540 0.2365
-2.000 0.2544 0.01939 0.01023 -0.1032 0.7469 0.2655
-1.750 0.2810 0.01927 0.01018 -0.1027 0.7416 0.2979
-1.500 0.3138 0.01900 0.00990 -0.1032 0.7373 0.3269
-1.250 0.3337 0.01905 0.00998 -0.1016 0.7290 0.3477
-1.000 0.3630 0.01885 0.00976 -0.1015 0.7223 0.3717
-0.750 0.3913 0.01870 0.00957 -0.1012 0.7152 0.3948
-0.500 0.4151 0.01863 0.00950 -0.1001 0.7064 0.4156
-0.250 0.4493 0.01833 0.00917 -0.1008 0.7006 0.4392
0.000 0.4678 0.01843 0.00934 -0.0990 0.6917 0.4603
0.250 0.4969 0.01830 0.00924 -0.0989 0.6858 0.4917
0.500 0.5246 0.01814 0.00918 -0.0986 0.6801 0.5294
0.750 0.5452 0.01808 0.00931 -0.0971 0.6723 0.5707
1.000 0.5737 0.01772 0.00920 -0.0968 0.6665 0.6384
1.250 0.6619 0.01714 0.00927 -0.1083 0.6582 1.0000
1.500 0.6852 0.01725 0.00925 -0.1073 0.6506 1.0000
1.750 0.7096 0.01734 0.00921 -0.1064 0.6435 1.0000
2.000 0.7288 0.01753 0.00933 -0.1047 0.6345 1.0000
2.250 0.7550 0.01756 0.00924 -0.1041 0.6270 1.0000
2.500 0.7722 0.01778 0.00942 -0.1021 0.6169 1.0000
2.750 0.7966 0.01785 0.00939 -0.1012 0.6084 1.0000
3.000 0.8149 0.01803 0.00953 -0.0993 0.5977 1.0000
3.250 0.8351 0.01818 0.00962 -0.0977 0.5870 1.0000
3.500 0.8581 0.01824 0.00959 -0.0965 0.5762 1.0000
3.750 0.8741 0.01847 0.00981 -0.0943 0.5631 1.0000
4.000 0.8923 0.01865 0.00994 -0.0924 0.5499 1.0000
4.250 0.9107 0.01882 0.01004 -0.0905 0.5358 1.0000
4.500 0.9282 0.01901 0.01016 -0.0884 0.5205 1.0000
4.750 0.9447 0.01924 0.01030 -0.0863 0.5039 1.0000
5.000 0.9606 0.01950 0.01047 -0.0840 0.4865 1.0000
5.250 0.9752 0.01980 0.01065 -0.0815 0.4692 1.0000
5.500 0.9892 0.02015 0.01087 -0.0790 0.4521 1.0000
5.750 1.0033 0.02055 0.01115 -0.0766 0.4359 1.0000
6.000 1.0179 0.02100 0.01147 -0.0744 0.4213 1.0000
6.250 1.0323 0.02150 0.01185 -0.0722 0.4077 1.0000
6.500 1.0470 0.02204 0.01230 -0.0702 0.3950 1.0000
6.750 1.0626 0.02258 0.01276 -0.0683 0.3840 1.0000
7.000 1.0780 0.02316 0.01323 -0.0665 0.3733 1.0000
7.250 1.0933 0.02376 0.01378 -0.0648 0.3634 1.0000
7.750 1.1244 0.02500 0.01492 -0.0615 0.3454 1.0000
8.000 1.1412 0.02562 0.01544 -0.0600 0.3376 1.0000
8.250 1.1561 0.02629 0.01614 -0.0584 0.3297 1.0000
8.500 1.1719 0.02695 0.01677 -0.0570 0.3224 1.0000
8.750 1.1879 0.02764 0.01744 -0.0556 0.3155 1.0000
9.000 1.2024 0.02836 0.01820 -0.0540 0.3085 1.0000
9.250 1.2195 0.02904 0.01881 -0.0528 0.3025 1.0000
9.500 1.2332 0.02983 0.01969 -0.0513 0.2961 1.0000
9.750 1.2472 0.03062 0.02052 -0.0499 0.2899 1.0000
10.000 1.2641 0.03134 0.02118 -0.0488 0.2845 1.0000
10.250 1.2750 0.03228 0.02224 -0.0471 0.2781 1.0000
10.500 1.2869 0.03319 0.02321 -0.0456 0.2721 1.0000
10.750 1.3011 0.03403 0.02400 -0.0444 0.2666 1.0000
11.000 1.3100 0.03514 0.02526 -0.0427 0.2603 1.0000
11.250 1.3204 0.03618 0.02635 -0.0413 0.2546 1.0000
11.500 1.3330 0.03715 0.02731 -0.0401 0.2496 1.0000
11.750 1.3411 0.03842 0.02874 -0.0386 0.2437 1.0000
12.000 1.3505 0.03962 0.02999 -0.0373 0.2386 1.0000
12.250 1.3625 0.04066 0.03098 -0.0362 0.2341 1.0000
12.500 1.3689 0.04217 0.03268 -0.0349 0.2287 1.0000
12.750 1.3763 0.04359 0.03419 -0.0336 0.2236 1.0000
13.000 1.3859 0.04483 0.03542 -0.0326 0.2194 1.0000
13.250 1.3917 0.04649 0.03720 -0.0314 0.2146 1.0000
13.500 1.3967 0.04822 0.03905 -0.0304 0.2098 1.0000
13.750 1.4039 0.04975 0.04063 -0.0294 0.2058 1.0000
14.000 1.4131 0.05119 0.04208 -0.0286 0.2022 1.0000
14.250 1.4156 0.05333 0.04440 -0.0277 0.1982 1.0000
14.500 1.4204 0.05528 0.04646 -0.0269 0.1945 1.0000
14.750 1.4270 0.05705 0.04829 -0.0262 0.1914 1.0000
15.000 1.4388 0.05833 0.04957 -0.0256 0.1886 1.0000
15.250 1.4384 0.06094 0.05236 -0.0250 0.1855 1.0000
15.500 1.4367 0.06372 0.05532 -0.0246 0.1823 1.0000
15.750 1.4382 0.06619 0.05791 -0.0242 0.1793 1.0000
16.000 1.4433 0.06823 0.06001 -0.0238 0.1765 1.0000
16.250 1.4562 0.06939 0.06114 -0.0234 0.1738 1.0000
16.500 1.4428 0.07378 0.06580 -0.0235 0.1712 1.0000
16.750 1.4312 0.07809 0.07032 -0.0239 0.1684 1.0000
17.000 1.4236 0.08197 0.07436 -0.0243 0.1656 1.0000
17.250 1.4256 0.08453 0.07696 -0.0245 0.1625 1.0000
17.500 1.4366 0.08586 0.07826 -0.0243 0.1595 1.0000
17.750 1.4035 0.09369 0.08641 -0.0265 0.1571 1.0000
18.000 1.3620 0.10338 0.09640 -0.0298 0.1550 1.0000
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