GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 100,000 Max Cl/Cd: 58.54 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe117-il-100000-n5.txt Download as CSV file: xf-goe117-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 117 (MVA MK.4) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3341 0.09122 0.08661 -0.0410 1.0000 0.0305
-8.000 -0.3409 0.08882 0.08431 -0.0401 1.0000 0.0303
-7.750 -0.3535 0.08686 0.08247 -0.0383 1.0000 0.0306
-7.500 -0.3699 0.08547 0.08120 -0.0353 1.0000 0.0302
-7.250 -0.3530 0.07981 0.07555 -0.0429 0.9901 0.0301
-7.000 -0.3346 0.07376 0.06948 -0.0512 0.9798 0.0296
-6.750 -0.3151 0.06727 0.06295 -0.0600 0.9693 0.0293
-6.500 -0.2932 0.06012 0.05571 -0.0693 0.9589 0.0291
-6.250 -0.2673 0.05114 0.04652 -0.0801 0.9495 0.0291
-6.000 -0.2391 0.04018 0.03495 -0.0910 0.9407 0.0303
-5.750 -0.2124 0.03350 0.02734 -0.0960 0.9318 0.0326
-5.500 -0.1797 0.02938 0.02228 -0.0990 0.9258 0.0340
-5.250 -0.1540 0.02647 0.01909 -0.1001 0.9173 0.0373
-5.000 -0.1201 0.02452 0.01671 -0.1019 0.9114 0.0417
-4.750 -0.0909 0.02281 0.01452 -0.1022 0.9025 0.0449
-4.500 -0.0572 0.02117 0.01262 -0.1038 0.8965 0.0499
-4.250 -0.0290 0.02007 0.01132 -0.1038 0.8866 0.0528
-4.000 0.0024 0.01925 0.01024 -0.1045 0.8780 0.0579
-3.750 0.0334 0.01831 0.00912 -0.1050 0.8691 0.0609
-3.500 0.0614 0.01758 0.00827 -0.1050 0.8582 0.0637
-3.250 0.0905 0.01699 0.00752 -0.1051 0.8476 0.0681
-3.000 0.1204 0.01643 0.00682 -0.1053 0.8376 0.0752
-2.750 0.1487 0.01577 0.00629 -0.1054 0.8265 0.0983
-2.500 0.1761 0.01543 0.00602 -0.1052 0.8140 0.1650
-2.250 0.2034 0.01525 0.00592 -0.1051 0.8013 0.2091
-2.000 0.2310 0.01525 0.00589 -0.1050 0.7885 0.2503
-1.750 0.2585 0.01518 0.00573 -0.1048 0.7760 0.2731
-1.500 0.2862 0.01509 0.00554 -0.1046 0.7639 0.2957
-1.250 0.3136 0.01492 0.00534 -0.1044 0.7520 0.3187
-1.000 0.3408 0.01476 0.00512 -0.1042 0.7400 0.3368
-0.750 0.3676 0.01462 0.00495 -0.1039 0.7279 0.3555
-0.500 0.3946 0.01448 0.00481 -0.1037 0.7171 0.3794
-0.250 0.4216 0.01432 0.00471 -0.1036 0.7076 0.4155
0.000 0.4475 0.01406 0.00465 -0.1032 0.6983 0.4887
0.250 0.4929 0.01299 0.00457 -0.1063 0.6892 1.0000
0.500 0.5199 0.01313 0.00451 -0.1060 0.6815 1.0000
0.750 0.5458 0.01329 0.00456 -0.1057 0.6731 1.0000
1.000 0.5726 0.01346 0.00458 -0.1054 0.6663 1.0000
1.250 0.5985 0.01364 0.00469 -0.1051 0.6587 1.0000
1.500 0.6254 0.01383 0.00476 -0.1049 0.6526 1.0000
1.750 0.6511 0.01404 0.00496 -0.1045 0.6455 1.0000
2.000 0.6779 0.01425 0.00510 -0.1043 0.6398 1.0000
2.250 0.7035 0.01449 0.00533 -0.1039 0.6332 1.0000
2.500 0.7298 0.01472 0.00556 -0.1037 0.6272 1.0000
2.750 0.7558 0.01497 0.00581 -0.1034 0.6211 1.0000
3.000 0.7814 0.01523 0.00610 -0.1030 0.6147 1.0000
3.250 0.8081 0.01549 0.00636 -0.1028 0.6092 1.0000
3.500 0.8328 0.01577 0.00677 -0.1023 0.6024 1.0000
3.750 0.8592 0.01605 0.00710 -0.1020 0.5970 1.0000
4.000 0.8842 0.01637 0.00753 -0.1016 0.5911 1.0000
4.250 0.9096 0.01667 0.00799 -0.1011 0.5851 1.0000
4.500 0.9333 0.01690 0.00831 -0.1002 0.5737 1.0000
4.750 0.9549 0.01693 0.00832 -0.0986 0.5522 1.0000
5.000 0.9735 0.01699 0.00846 -0.0965 0.5269 1.0000
5.250 0.9930 0.01711 0.00870 -0.0947 0.5021 1.0000
5.500 1.0087 0.01723 0.00886 -0.0922 0.4589 1.0000
5.750 1.0113 0.01814 0.00902 -0.0875 0.3184 1.0000
6.000 0.9940 0.02159 0.01099 -0.0814 0.0919 1.0000
6.250 1.0019 0.02308 0.01236 -0.0785 0.0618 1.0000
6.500 1.0125 0.02427 0.01364 -0.0759 0.0503 1.0000
6.750 1.0211 0.02549 0.01499 -0.0730 0.0423 1.0000
7.000 1.0258 0.02675 0.01637 -0.0697 0.0383 1.0000
7.250 1.0257 0.02825 0.01797 -0.0658 0.0356 1.0000
7.500 1.0308 0.02952 0.01945 -0.0628 0.0322 1.0000
7.750 1.0347 0.03096 0.02097 -0.0600 0.0297 1.0000
8.000 1.0375 0.03265 0.02269 -0.0572 0.0280 1.0000
8.250 1.0439 0.03466 0.02463 -0.0547 0.0266 1.0000
8.500 1.0622 0.03603 0.02614 -0.0532 0.0249 1.0000
8.750 1.0848 0.03758 0.02783 -0.0522 0.0224 1.0000
9.000 1.1188 0.03971 0.03011 -0.0522 0.0209 1.0000
9.250 1.1562 0.04244 0.03304 -0.0531 0.0198 1.0000
9.500 1.1774 0.04485 0.03573 -0.0525 0.0186 1.0000
9.750 1.1915 0.04738 0.03842 -0.0514 0.0174 1.0000
10.000 1.2093 0.05228 0.04362 -0.0512 0.0164 1.0000
10.250 1.2153 0.05517 0.04685 -0.0488 0.0162 1.0000
10.500 1.2171 0.05822 0.05023 -0.0463 0.0161 1.0000
10.750 1.2144 0.06137 0.05370 -0.0436 0.0160 1.0000
11.000 1.2087 0.06462 0.05724 -0.0411 0.0160 1.0000
11.250 1.2000 0.06806 0.06096 -0.0388 0.0160 1.0000
11.500 1.1891 0.07168 0.06483 -0.0370 0.0160 1.0000
11.750 1.1763 0.07555 0.06896 -0.0357 0.0160 1.0000
12.000 1.1622 0.07970 0.07333 -0.0349 0.0160 1.0000
12.250 1.1467 0.08415 0.07800 -0.0347 0.0161 1.0000
12.500 1.1306 0.08896 0.08302 -0.0351 0.0161 1.0000
12.750 1.1135 0.09412 0.08837 -0.0361 0.0162 1.0000
13.000 1.0965 0.09966 0.09408 -0.0378 0.0163 1.0000
13.250 1.0798 0.10558 0.10015 -0.0400 0.0164 1.0000
13.750 0.8923 0.11062 0.10611 -0.0393 0.0171 1.0000
14.000 0.8672 0.11789 0.11359 -0.0440 0.0174 1.0000
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Polar data table (+)
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