GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.2 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe137-il-1000000-n5.txt Download as CSV file: xf-goe137-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4120 0.11137 0.10980 -0.0106 1.0000 0.0043
-9.250 -0.5636 0.02140 0.01839 -0.0840 0.9568 0.0054
-9.000 -0.5429 0.01856 0.01516 -0.0843 0.9489 0.0056
-8.750 -0.5197 0.01697 0.01332 -0.0842 0.9402 0.0058
-8.500 -0.4954 0.01579 0.01192 -0.0840 0.9316 0.0060
-8.250 -0.4710 0.01465 0.01057 -0.0837 0.9223 0.0064
-8.000 -0.4455 0.01379 0.00955 -0.0835 0.9120 0.0068
-7.750 -0.4197 0.01310 0.00871 -0.0833 0.9003 0.0073
-7.500 -0.3937 0.01251 0.00797 -0.0830 0.8864 0.0078
-7.250 -0.3674 0.01199 0.00727 -0.0827 0.8703 0.0083
-7.000 -0.3411 0.01151 0.00663 -0.0824 0.8510 0.0091
-6.750 -0.3144 0.01112 0.00611 -0.0821 0.8278 0.0101
-6.500 -0.2877 0.01081 0.00563 -0.0819 0.8010 0.0112
-6.250 -0.2606 0.01056 0.00520 -0.0817 0.7740 0.0123
-6.000 -0.2329 0.01058 0.00516 -0.0816 0.7494 0.0140
-5.750 -0.2050 0.01057 0.00507 -0.0815 0.7295 0.0155
-5.500 -0.1771 0.01046 0.00483 -0.0815 0.7129 0.0166
-5.250 -0.1489 0.01049 0.00483 -0.0815 0.6988 0.0177
-5.000 -0.1205 0.01059 0.00490 -0.0815 0.6860 0.0186
-4.750 -0.0922 0.01062 0.00487 -0.0815 0.6739 0.0196
-4.500 -0.0639 0.01059 0.00478 -0.0815 0.6621 0.0208
-4.250 -0.0356 0.01052 0.00463 -0.0816 0.6514 0.0219
-4.000 -0.0073 0.01045 0.00448 -0.0816 0.6417 0.0227
-3.750 0.0210 0.01041 0.00438 -0.0816 0.6327 0.0232
-3.500 0.0495 0.01037 0.00429 -0.0817 0.6249 0.0236
-3.250 0.0779 0.01035 0.00420 -0.0817 0.6165 0.0238
-3.000 0.1054 0.00946 0.00318 -0.0818 0.6068 0.0255
-2.750 0.1336 0.00925 0.00289 -0.0818 0.5962 0.0265
-2.500 0.1618 0.00908 0.00265 -0.0819 0.5848 0.0271
-2.250 0.1901 0.00891 0.00242 -0.0819 0.5750 0.0275
-2.000 0.2185 0.00877 0.00222 -0.0820 0.5667 0.0279
-1.750 0.2469 0.00864 0.00203 -0.0820 0.5573 0.0282
-1.500 0.2753 0.00852 0.00186 -0.0821 0.5480 0.0285
-1.250 0.3037 0.00843 0.00171 -0.0822 0.5386 0.0287
-1.000 0.3321 0.00836 0.00158 -0.0822 0.5273 0.0291
-0.750 0.3604 0.00832 0.00148 -0.0823 0.5139 0.0297
-0.500 0.3887 0.00830 0.00138 -0.0824 0.4995 0.0300
-0.250 0.4169 0.00829 0.00130 -0.0824 0.4849 0.0303
0.000 0.4451 0.00830 0.00125 -0.0825 0.4713 0.0309
0.250 0.4733 0.00832 0.00121 -0.0825 0.4586 0.0319
0.500 0.5014 0.00837 0.00120 -0.0826 0.4432 0.0333
0.750 0.5294 0.00843 0.00120 -0.0826 0.4291 0.0351
1.000 0.5575 0.00847 0.00121 -0.0827 0.4174 0.0439
1.250 0.5855 0.00841 0.00126 -0.0828 0.4056 0.1065
1.500 0.6134 0.00846 0.00132 -0.0829 0.3936 0.1291
1.750 0.6414 0.00850 0.00138 -0.0830 0.3821 0.1505
2.000 0.6694 0.00850 0.00145 -0.0831 0.3723 0.1919
2.250 0.6972 0.00839 0.00156 -0.0833 0.3630 0.3086
2.750 0.7488 0.00710 0.00182 -0.0828 0.3440 1.0000
3.000 0.7764 0.00726 0.00192 -0.0829 0.3331 1.0000
3.250 0.8040 0.00742 0.00202 -0.0829 0.3222 1.0000
3.500 0.8313 0.00763 0.00215 -0.0829 0.3067 1.0000
3.750 0.8583 0.00786 0.00229 -0.0828 0.2869 1.0000
4.000 0.8851 0.00811 0.00245 -0.0828 0.2670 1.0000
4.250 0.9111 0.00848 0.00265 -0.0826 0.2357 1.0000
4.500 0.9347 0.00919 0.00305 -0.0822 0.1769 1.0000
4.750 0.9612 0.00947 0.00326 -0.0821 0.1661 1.0000
5.000 0.9878 0.00971 0.00348 -0.0820 0.1586 1.0000
5.250 1.0144 0.00994 0.00369 -0.0819 0.1515 1.0000
5.500 1.0411 0.01015 0.00388 -0.0818 0.1447 1.0000
5.750 1.0673 0.01043 0.00412 -0.0817 0.1345 1.0000
6.000 1.0896 0.01119 0.00457 -0.0811 0.0828 1.0000
6.250 1.1134 0.01175 0.00503 -0.0806 0.0592 1.0000
6.500 1.1339 0.01273 0.00576 -0.0797 0.0154 1.0000
6.750 1.1589 0.01308 0.00614 -0.0794 0.0114 1.0000
7.000 1.1841 0.01339 0.00648 -0.0791 0.0105 1.0000
7.250 1.2087 0.01375 0.00687 -0.0787 0.0093 1.0000
7.500 1.2326 0.01419 0.00733 -0.0782 0.0080 1.0000
7.750 1.2566 0.01459 0.00777 -0.0778 0.0073 1.0000
8.000 1.2804 0.01498 0.00820 -0.0773 0.0067 1.0000
8.250 1.3037 0.01542 0.00866 -0.0768 0.0061 1.0000
8.500 1.3263 0.01591 0.00918 -0.0762 0.0056 1.0000
8.750 1.3473 0.01654 0.00986 -0.0753 0.0051 1.0000
9.000 1.3693 0.01704 0.01040 -0.0746 0.0049 1.0000
9.250 1.3906 0.01756 0.01098 -0.0738 0.0047 1.0000
9.500 1.4114 0.01811 0.01158 -0.0729 0.0043 1.0000
9.750 1.4316 0.01867 0.01218 -0.0720 0.0041 1.0000
10.000 1.4509 0.01926 0.01282 -0.0710 0.0038 1.0000
10.250 1.4682 0.01999 0.01359 -0.0697 0.0036 1.0000
10.500 1.4816 0.02098 0.01467 -0.0678 0.0034 1.0000
10.750 1.4965 0.02172 0.01548 -0.0662 0.0033 1.0000
11.000 1.5073 0.02254 0.01637 -0.0639 0.0032 1.0000
11.250 1.5170 0.02346 0.01737 -0.0616 0.0031 1.0000
11.500 1.5257 0.02450 0.01852 -0.0594 0.0030 1.0000
11.750 1.5331 0.02570 0.01980 -0.0573 0.0029 1.0000
12.000 1.5399 0.02703 0.02122 -0.0554 0.0028 1.0000
12.250 1.5457 0.02853 0.02281 -0.0537 0.0028 1.0000
12.500 1.5511 0.03018 0.02456 -0.0522 0.0027 1.0000
12.750 1.5549 0.03208 0.02655 -0.0510 0.0026 1.0000
13.000 1.5585 0.03415 0.02872 -0.0500 0.0026 1.0000
13.250 1.5615 0.03640 0.03107 -0.0493 0.0025 1.0000
13.500 1.5632 0.03895 0.03371 -0.0489 0.0024 1.0000
13.750 1.5639 0.04169 0.03654 -0.0486 0.0024 1.0000
14.000 1.5632 0.04469 0.03965 -0.0486 0.0024 1.0000
14.250 1.5608 0.04799 0.04305 -0.0487 0.0023 1.0000
14.500 1.5561 0.05162 0.04678 -0.0489 0.0023 1.0000
14.750 1.5496 0.05557 0.05084 -0.0493 0.0022 1.0000
15.000 1.5406 0.05993 0.05534 -0.0499 0.0022 1.0000
15.250 1.5295 0.06472 0.06025 -0.0508 0.0022 1.0000
15.500 1.5164 0.06998 0.06564 -0.0519 0.0021 1.0000
15.750 1.5020 0.07557 0.07136 -0.0533 0.0021 1.0000
16.000 1.4876 0.08134 0.07725 -0.0549 0.0021 1.0000
16.250 1.4790 0.08637 0.08239 -0.0564 0.0021 1.0000
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