GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 200,000 Max Cl/Cd: 84.37 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe124-il-200000.txt Download as CSV file: xf-goe124-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2817 0.09363 0.09030 -0.0268 1.0000 0.0346
-7.500 -0.2824 0.09182 0.08857 -0.0279 1.0000 0.0358
-7.250 -0.2982 0.09162 0.08850 -0.0264 1.0000 0.0362
-7.000 -0.2665 0.08824 0.08508 -0.0444 0.9909 0.0367
-6.750 -0.2452 0.08224 0.07908 -0.0474 0.9861 0.0372
-6.500 -0.2242 0.07788 0.07472 -0.0476 0.9831 0.0379
-6.250 -0.1966 0.07389 0.07071 -0.0521 0.9754 0.0390
-6.000 -0.1626 0.06967 0.06645 -0.0595 0.9685 0.0407
-5.750 -0.0979 0.06496 0.06149 -0.0801 0.9565 0.0449
-5.500 -0.0663 0.05956 0.05598 -0.0871 0.9449 0.0456
-5.250 -0.0519 0.05623 0.05268 -0.0861 0.9339 0.0464
-5.000 -0.0324 0.05352 0.04995 -0.0868 0.9224 0.0475
-4.750 -0.0095 0.05086 0.04720 -0.0887 0.9100 0.0492
-4.500 0.0183 0.04800 0.04421 -0.0919 0.8971 0.0519
-4.250 0.0659 0.04358 0.03936 -0.1007 0.8857 0.0564
-4.000 0.0832 0.04118 0.03696 -0.1002 0.8752 0.0576
-3.750 0.1059 0.03911 0.03482 -0.1008 0.8643 0.0596
-3.500 0.1347 0.03691 0.03246 -0.1026 0.8535 0.0632
-3.250 0.1742 0.03378 0.02884 -0.1065 0.8444 0.0695
-3.000 0.1966 0.03189 0.02696 -0.1066 0.8333 0.0717
-2.750 0.2244 0.03034 0.02526 -0.1073 0.8218 0.0774
-2.500 0.2553 0.02823 0.02285 -0.1087 0.8113 0.0857
-2.000 0.3124 0.02525 0.01952 -0.1101 0.7891 0.1023
-1.750 0.3421 0.02399 0.01804 -0.1108 0.7799 0.1161
-1.500 0.3705 0.02288 0.01680 -0.1114 0.7710 0.1318
-1.250 0.3982 0.02192 0.01578 -0.1119 0.7618 0.1504
-1.000 0.4254 0.02107 0.01485 -0.1122 0.7536 0.1799
0.000 0.5607 0.01590 0.00798 -0.1120 0.7212 0.0766
0.250 0.5905 0.01525 0.00712 -0.1118 0.7117 0.0706
0.500 0.6191 0.01499 0.00673 -0.1115 0.7033 0.0688
0.750 0.6476 0.01450 0.00621 -0.1113 0.6943 0.0691
1.000 0.6760 0.01401 0.00577 -0.1114 0.6856 0.0718
1.250 0.7044 0.01372 0.00546 -0.1112 0.6770 0.0726
1.500 0.7330 0.01350 0.00528 -0.1113 0.6674 0.0739
1.750 0.7615 0.01336 0.00509 -0.1112 0.6588 0.0766
2.000 0.7899 0.01328 0.00499 -0.1111 0.6482 0.0808
2.250 0.8183 0.01319 0.00490 -0.1111 0.6378 0.0940
2.500 0.8376 0.01145 0.00492 -0.1091 0.6291 1.0000
2.750 0.8655 0.01158 0.00493 -0.1089 0.6175 1.0000
3.000 0.8932 0.01173 0.00498 -0.1087 0.6059 1.0000
3.250 0.9206 0.01187 0.00502 -0.1085 0.5934 1.0000
3.500 0.9478 0.01202 0.00507 -0.1082 0.5799 1.0000
3.750 0.9748 0.01217 0.00515 -0.1079 0.5655 1.0000
4.000 1.0018 0.01233 0.00525 -0.1077 0.5507 1.0000
4.250 1.0286 0.01252 0.00538 -0.1074 0.5355 1.0000
4.500 1.0553 0.01272 0.00555 -0.1071 0.5197 1.0000
4.750 1.0818 0.01295 0.00573 -0.1069 0.5048 1.0000
5.000 1.1084 0.01322 0.00595 -0.1067 0.4913 1.0000
5.250 1.1348 0.01349 0.00621 -0.1064 0.4775 1.0000
5.500 1.1610 0.01378 0.00649 -0.1062 0.4636 1.0000
5.750 1.1871 0.01407 0.00678 -0.1059 0.4507 1.0000
6.000 1.2130 0.01439 0.00710 -0.1056 0.4386 1.0000
6.250 1.2387 0.01473 0.00744 -0.1053 0.4275 1.0000
6.750 1.2891 0.01540 0.00813 -0.1045 0.4023 1.0000
7.000 1.3141 0.01574 0.00852 -0.1041 0.3897 1.0000
7.250 1.3387 0.01611 0.00895 -0.1037 0.3771 1.0000
7.500 1.3626 0.01649 0.00938 -0.1031 0.3625 1.0000
7.750 1.3852 0.01692 0.00980 -0.1024 0.3436 1.0000
8.000 1.4070 0.01739 0.01028 -0.1016 0.3208 1.0000
8.250 1.4275 0.01793 0.01083 -0.1006 0.2905 1.0000
8.500 1.4456 0.01868 0.01144 -0.0994 0.2395 1.0000
8.750 1.4564 0.02018 0.01249 -0.0974 0.1781 1.0000
9.000 1.4679 0.02161 0.01374 -0.0955 0.1542 1.0000
9.250 1.4805 0.02285 0.01495 -0.0937 0.1402 1.0000
9.500 1.4939 0.02395 0.01607 -0.0919 0.1285 1.0000
9.750 1.5064 0.02503 0.01721 -0.0901 0.1179 1.0000
10.000 1.5166 0.02617 0.01840 -0.0879 0.1067 1.0000
10.250 1.5248 0.02727 0.01954 -0.0855 0.0917 1.0000
10.500 1.5283 0.02882 0.02099 -0.0828 0.0676 1.0000
10.750 1.5241 0.03112 0.02316 -0.0797 0.0527 1.0000
11.000 1.5222 0.03344 0.02554 -0.0773 0.0458 1.0000
11.500 1.5173 0.03868 0.03093 -0.0736 0.0394 1.0000
11.750 1.5170 0.04129 0.03364 -0.0723 0.0372 1.0000
12.000 1.5132 0.04435 0.03676 -0.0712 0.0354 1.0000
12.250 1.5069 0.04776 0.04023 -0.0700 0.0340 1.0000
12.500 1.5083 0.05043 0.04306 -0.0691 0.0326 1.0000
12.750 1.5079 0.05332 0.04608 -0.0683 0.0314 1.0000
13.000 1.5071 0.05629 0.04915 -0.0675 0.0304 1.0000
13.250 1.5060 0.05928 0.05221 -0.0668 0.0296 1.0000
13.500 1.5048 0.06228 0.05527 -0.0659 0.0288 1.0000
13.750 1.5047 0.06508 0.05811 -0.0646 0.0280 1.0000
14.000 1.5074 0.06763 0.06074 -0.0629 0.0274 1.0000
14.250 1.5089 0.07052 0.06381 -0.0622 0.0269 1.0000
14.500 1.5096 0.07358 0.06704 -0.0617 0.0263 1.0000
14.750 1.5093 0.07680 0.07045 -0.0614 0.0256 1.0000
15.000 1.5083 0.08017 0.07397 -0.0613 0.0250 1.0000
15.250 1.5061 0.08376 0.07772 -0.0614 0.0244 1.0000
15.500 1.5038 0.08746 0.08159 -0.0615 0.0241 1.0000
15.750 1.4999 0.09145 0.08575 -0.0618 0.0238 1.0000
16.000 1.4947 0.09572 0.09019 -0.0625 0.0235 1.0000
16.250 1.4881 0.10033 0.09498 -0.0634 0.0233 1.0000
16.500 1.4799 0.10532 0.10016 -0.0648 0.0232 1.0000
16.750 1.4697 0.11080 0.10584 -0.0668 0.0231 1.0000
17.000 1.4571 0.11691 0.11217 -0.0693 0.0230 1.0000
17.250 1.4419 0.12381 0.11931 -0.0728 0.0231 1.0000
17.500 1.4239 0.13165 0.12741 -0.0772 0.0232 1.0000
17.750 1.4025 0.14079 0.13682 -0.0829 0.0234 1.0000
18.000 1.3708 0.15322 0.14959 -0.0915 0.0239 1.0000
18.250 1.3187 0.17304 0.16978 -0.1060 0.0249 1.0000
18.500 1.2334 0.21228 0.20916 -0.1314 0.0283 1.0000
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Polar data table (+)
Polar graphs
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