GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 100,000 Max Cl/Cd: 56.87 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe137-il-100000.txt Download as CSV file: xf-goe137-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 137 (MVA H.15) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3443 0.09760 0.09295 -0.0228 1.0000 0.0765
-7.750 -0.3523 0.09631 0.09178 -0.0272 1.0000 0.0785
-7.500 -0.3546 0.09472 0.09026 -0.0373 1.0000 0.0792
-7.250 -0.3412 0.08864 0.08423 -0.0276 1.0000 0.0819
-7.000 -0.3345 0.08574 0.08135 -0.0269 1.0000 0.0850
-6.750 -0.3325 0.08317 0.07885 -0.0283 1.0000 0.0886
-6.500 -0.3345 0.08184 0.07753 -0.0378 1.0000 0.0924
-6.250 -0.3340 0.07794 0.07370 -0.0377 1.0000 0.0936
-6.000 -0.3323 0.07488 0.07074 -0.0320 1.0000 0.0957
-5.750 -0.3317 0.07270 0.06862 -0.0299 1.0000 0.0987
-5.500 -0.3318 0.07065 0.06661 -0.0301 1.0000 0.1029
-5.250 -0.3265 0.06828 0.06408 -0.0369 1.0000 0.1077
-5.000 -0.3309 0.06580 0.06176 -0.0321 1.0000 0.1096
-4.750 -0.2909 0.06173 0.05744 -0.0417 0.9944 0.1227
-4.500 -0.2606 0.05769 0.05346 -0.0435 0.9872 0.1302
-4.250 -0.2155 0.05308 0.04864 -0.0515 0.9791 0.1425
-4.000 -0.1694 0.04898 0.04435 -0.0587 0.9715 0.1586
-3.750 -0.1243 0.04538 0.04046 -0.0657 0.9617 0.1825
-3.500 -0.0793 0.04170 0.03667 -0.0708 0.9559 0.2003
-3.250 -0.0397 0.03887 0.03365 -0.0750 0.9454 0.2280
-2.750 0.0831 0.02709 0.01963 -0.0875 0.9321 0.1019
-2.500 0.1319 0.02465 0.01668 -0.0911 0.9263 0.1013
-2.250 0.1697 0.02297 0.01461 -0.0925 0.9150 0.1017
-2.000 0.2068 0.02154 0.01287 -0.0936 0.9041 0.1022
-1.750 0.2442 0.02034 0.01144 -0.0946 0.8943 0.1048
-1.500 0.2781 0.01934 0.01039 -0.0951 0.8837 0.1113
-1.250 0.3077 0.01871 0.00969 -0.0948 0.8708 0.1203
-1.000 0.3357 0.01794 0.00902 -0.0942 0.8583 0.1310
-0.750 0.3632 0.01720 0.00838 -0.0934 0.8461 0.1572
-0.500 0.3960 0.01410 0.00765 -0.0933 0.8364 1.0000
-0.250 0.4235 0.01412 0.00731 -0.0924 0.8244 1.0000
0.000 0.4495 0.01422 0.00716 -0.0915 0.8110 1.0000
0.250 0.4754 0.01434 0.00706 -0.0907 0.7977 1.0000
0.500 0.5014 0.01448 0.00702 -0.0899 0.7845 1.0000
0.750 0.5274 0.01463 0.00701 -0.0891 0.7715 1.0000
1.000 0.5534 0.01481 0.00703 -0.0884 0.7587 1.0000
1.250 0.5795 0.01499 0.00707 -0.0876 0.7458 1.0000
1.500 0.6055 0.01518 0.00712 -0.0868 0.7327 1.0000
1.750 0.6314 0.01538 0.00718 -0.0861 0.7193 1.0000
2.000 0.6574 0.01558 0.00727 -0.0853 0.7057 1.0000
2.250 0.6833 0.01578 0.00736 -0.0845 0.6920 1.0000
2.500 0.7091 0.01603 0.00752 -0.0838 0.6779 1.0000
2.750 0.7349 0.01630 0.00773 -0.0832 0.6643 1.0000
3.000 0.7608 0.01658 0.00799 -0.0827 0.6509 1.0000
3.250 0.7865 0.01685 0.00821 -0.0821 0.6373 1.0000
3.500 0.8124 0.01712 0.00845 -0.0815 0.6241 1.0000
3.750 0.8383 0.01739 0.00872 -0.0810 0.6114 1.0000
4.000 0.8642 0.01764 0.00894 -0.0804 0.5986 1.0000
4.250 0.8902 0.01786 0.00913 -0.0798 0.5860 1.0000
4.500 0.9165 0.01807 0.00930 -0.0792 0.5741 1.0000
4.750 0.9419 0.01837 0.00968 -0.0787 0.5612 1.0000
5.000 0.9674 0.01869 0.01006 -0.0783 0.5488 1.0000
5.250 0.9929 0.01901 0.01044 -0.0778 0.5367 1.0000
5.500 1.0185 0.01930 0.01078 -0.0772 0.5248 1.0000
5.750 1.0442 0.01958 0.01111 -0.0767 0.5125 1.0000
6.000 1.0698 0.01984 0.01141 -0.0761 0.4995 1.0000
6.250 1.0946 0.02010 0.01173 -0.0754 0.4848 1.0000
6.500 1.1188 0.02037 0.01208 -0.0745 0.4685 1.0000
6.750 1.1426 0.02066 0.01248 -0.0737 0.4511 1.0000
7.000 1.1660 0.02084 0.01265 -0.0726 0.4310 1.0000
7.250 1.1870 0.02101 0.01285 -0.0713 0.4059 1.0000
7.500 1.2075 0.02126 0.01308 -0.0699 0.3808 1.0000
7.750 1.2273 0.02158 0.01340 -0.0685 0.3555 1.0000
8.000 1.2464 0.02202 0.01394 -0.0672 0.3302 1.0000
8.250 1.2651 0.02252 0.01451 -0.0658 0.3056 1.0000
8.500 1.2828 0.02307 0.01512 -0.0644 0.2800 1.0000
8.750 1.2989 0.02370 0.01582 -0.0628 0.2491 1.0000
9.000 1.3101 0.02474 0.01670 -0.0608 0.2054 1.0000
9.250 1.3139 0.02663 0.01827 -0.0581 0.1530 1.0000
9.500 1.3078 0.02951 0.02049 -0.0545 0.0781 1.0000
9.750 1.3032 0.03194 0.02286 -0.0507 0.0641 1.0000
10.000 1.2974 0.03429 0.02523 -0.0472 0.0582 1.0000
10.250 1.2979 0.03634 0.02744 -0.0447 0.0541 1.0000
10.500 1.2971 0.03861 0.02981 -0.0425 0.0506 1.0000
10.750 1.2929 0.04132 0.03256 -0.0407 0.0481 1.0000
11.000 1.2929 0.04384 0.03520 -0.0391 0.0459 1.0000
11.250 1.2956 0.04623 0.03772 -0.0377 0.0439 1.0000
11.500 1.2996 0.04862 0.04023 -0.0363 0.0425 1.0000
11.750 1.3061 0.05088 0.04256 -0.0347 0.0412 1.0000
12.000 1.3163 0.05302 0.04474 -0.0330 0.0401 1.0000
12.250 1.3332 0.05508 0.04682 -0.0311 0.0391 1.0000
12.500 1.3622 0.05790 0.04969 -0.0292 0.0381 1.0000
12.750 1.3687 0.06114 0.05318 -0.0280 0.0375 1.0000
13.000 1.3665 0.06441 0.05677 -0.0270 0.0371 1.0000
13.250 1.3615 0.06806 0.06072 -0.0263 0.0367 1.0000
13.500 1.3535 0.07210 0.06508 -0.0260 0.0365 1.0000
13.750 1.3429 0.07656 0.06983 -0.0261 0.0364 1.0000
14.000 1.3301 0.08143 0.07497 -0.0266 0.0365 1.0000
14.250 1.3152 0.08672 0.08052 -0.0277 0.0367 1.0000
14.500 1.2986 0.09239 0.08642 -0.0294 0.0369 1.0000
14.750 1.2805 0.09849 0.09275 -0.0316 0.0371 1.0000
15.000 1.2616 0.10496 0.09942 -0.0344 0.0373 1.0000
15.250 1.2423 0.11188 0.10653 -0.0378 0.0375 1.0000
15.500 1.2238 0.11922 0.11403 -0.0415 0.0378 1.0000
15.750 1.2040 0.12691 0.12190 -0.0466 0.0381 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 137 (MVA H.15) AIRFOIL (goe137-il)