GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 200,000 Max Cl/Cd: 83.78 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe124-il-200000-n5.txt Download as CSV file: xf-goe124-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3353 0.12001 0.11642 -0.0179 1.0000 0.0241
-9.750 -0.3321 0.11750 0.11395 -0.0209 1.0000 0.0243
-9.500 -0.3282 0.11469 0.11116 -0.0235 1.0000 0.0243
-9.250 -0.3232 0.11159 0.10810 -0.0258 1.0000 0.0244
-9.000 -0.3117 0.10692 0.10345 -0.0252 1.0000 0.0246
-8.750 -0.3010 0.10331 0.09985 -0.0248 1.0000 0.0250
-8.500 -0.2927 0.10035 0.09693 -0.0256 1.0000 0.0254
-8.250 -0.2853 0.09758 0.09418 -0.0266 1.0000 0.0259
-8.000 -0.2785 0.09499 0.09164 -0.0277 1.0000 0.0269
-7.750 -0.2686 0.09214 0.08881 -0.0304 0.9868 0.0286
-7.500 -0.2492 0.08877 0.08543 -0.0401 0.9582 0.0301
-7.250 -0.2262 0.08470 0.08131 -0.0496 0.9382 0.0303
-7.000 -0.2040 0.08058 0.07712 -0.0566 0.9213 0.0305
-6.500 -0.1783 0.07266 0.06915 -0.0589 0.8938 0.0312
-6.250 -0.1657 0.07003 0.06648 -0.0584 0.8809 0.0320
-6.000 -0.1482 0.06712 0.06350 -0.0607 0.8680 0.0328
-5.750 -0.1276 0.06398 0.06028 -0.0642 0.8554 0.0338
-5.500 -0.1038 0.06069 0.05690 -0.0686 0.8432 0.0353
-5.250 -0.0507 0.05615 0.05205 -0.0826 0.8316 0.0387
-5.000 -0.0164 0.05228 0.04791 -0.0883 0.8215 0.0389
-4.750 0.0021 0.04780 0.04340 -0.0901 0.8113 0.0395
-4.500 0.0218 0.04520 0.04073 -0.0908 0.8013 0.0402
-4.000 0.0736 0.04036 0.03567 -0.0945 0.7822 0.0423
-3.750 0.1212 0.03773 0.03249 -0.1001 0.7739 0.0488
-3.500 0.1545 0.03537 0.02974 -0.1024 0.7649 0.0490
-3.250 0.1788 0.03142 0.02579 -0.1042 0.7563 0.0501
-3.000 0.2060 0.02948 0.02373 -0.1052 0.7467 0.0511
-2.750 0.2352 0.02770 0.02178 -0.1064 0.7362 0.0523
-2.500 0.2691 0.02504 0.01872 -0.1078 0.7264 0.0444
-2.250 0.3009 0.02319 0.01653 -0.1088 0.7156 0.0441
-1.750 0.3666 0.01985 0.01225 -0.1099 0.6951 0.0383
-1.500 0.3966 0.01865 0.01079 -0.1105 0.6860 0.0380
-1.250 0.4265 0.01770 0.00960 -0.1108 0.6782 0.0380
-1.000 0.4561 0.01692 0.00860 -0.1111 0.6699 0.0380
-0.750 0.4855 0.01628 0.00777 -0.1112 0.6623 0.0382
-0.500 0.5146 0.01581 0.00711 -0.1113 0.6546 0.0393
-0.250 0.5434 0.01507 0.00632 -0.1116 0.6470 0.0406
0.000 0.5720 0.01463 0.00579 -0.1117 0.6388 0.0409
0.250 0.6007 0.01424 0.00535 -0.1117 0.6307 0.0411
0.500 0.6291 0.01391 0.00498 -0.1117 0.6225 0.0414
0.750 0.6577 0.01362 0.00469 -0.1118 0.6144 0.0421
1.000 0.6861 0.01340 0.00446 -0.1119 0.6064 0.0429
1.250 0.7147 0.01322 0.00429 -0.1120 0.5979 0.0440
1.500 0.7430 0.01311 0.00416 -0.1121 0.5895 0.0454
1.750 0.7713 0.01306 0.00410 -0.1121 0.5797 0.0483
2.000 0.7997 0.01299 0.00400 -0.1122 0.5702 0.0508
2.250 0.8278 0.01296 0.00395 -0.1122 0.5600 0.0533
2.500 0.8559 0.01297 0.00394 -0.1122 0.5497 0.0572
2.750 0.8838 0.01299 0.00396 -0.1122 0.5394 0.0677
3.000 0.9030 0.01139 0.00412 -0.1105 0.5281 1.0000
3.250 0.9304 0.01157 0.00419 -0.1103 0.5143 1.0000
3.500 0.9576 0.01177 0.00429 -0.1102 0.4993 1.0000
3.750 0.9845 0.01198 0.00442 -0.1100 0.4835 1.0000
4.000 1.0113 0.01222 0.00457 -0.1098 0.4678 1.0000
4.250 1.0379 0.01247 0.00476 -0.1097 0.4525 1.0000
4.500 1.0643 0.01275 0.00497 -0.1094 0.4368 1.0000
4.750 1.0904 0.01305 0.00520 -0.1092 0.4216 1.0000
5.000 1.1166 0.01334 0.00546 -0.1090 0.4088 1.0000
5.250 1.1428 0.01364 0.00576 -0.1088 0.3981 1.0000
5.500 1.1686 0.01398 0.00607 -0.1085 0.3867 1.0000
5.750 1.1939 0.01434 0.00639 -0.1082 0.3749 1.0000
6.000 1.2194 0.01468 0.00675 -0.1079 0.3635 1.0000
6.250 1.2447 0.01504 0.00712 -0.1076 0.3529 1.0000
6.500 1.2695 0.01544 0.00751 -0.1072 0.3428 1.0000
6.750 1.2941 0.01583 0.00792 -0.1068 0.3311 1.0000
7.000 1.3183 0.01623 0.00837 -0.1064 0.3176 1.0000
7.250 1.3422 0.01666 0.00882 -0.1059 0.3035 1.0000
7.500 1.3659 0.01709 0.00929 -0.1054 0.2887 1.0000
7.750 1.3882 0.01762 0.00982 -0.1047 0.2661 1.0000
8.000 1.4072 0.01841 0.01043 -0.1037 0.2157 1.0000
8.250 1.4188 0.01995 0.01153 -0.1019 0.1576 1.0000
8.500 1.4345 0.02105 0.01254 -0.1005 0.1378 1.0000
8.750 1.4506 0.02204 0.01350 -0.0991 0.1248 1.0000
9.000 1.4667 0.02296 0.01445 -0.0977 0.1143 1.0000
9.250 1.4833 0.02378 0.01533 -0.0963 0.1059 1.0000
9.500 1.4971 0.02475 0.01632 -0.0946 0.0966 1.0000
9.750 1.5115 0.02561 0.01723 -0.0930 0.0865 1.0000
10.000 1.5232 0.02651 0.01819 -0.0910 0.0762 1.0000
10.250 1.5312 0.02764 0.01933 -0.0886 0.0644 1.0000
10.500 1.5354 0.02914 0.02077 -0.0861 0.0508 1.0000
10.750 1.5371 0.03096 0.02255 -0.0837 0.0376 1.0000
11.000 1.5374 0.03305 0.02462 -0.0815 0.0291 1.0000
11.250 1.5386 0.03520 0.02682 -0.0797 0.0249 1.0000
11.500 1.5397 0.03748 0.02917 -0.0781 0.0225 1.0000
11.750 1.5405 0.03991 0.03170 -0.0768 0.0210 1.0000
12.000 1.5421 0.04235 0.03431 -0.0757 0.0199 1.0000
12.250 1.5422 0.04503 0.03713 -0.0748 0.0189 1.0000
12.500 1.5408 0.04798 0.04021 -0.0740 0.0180 1.0000
12.750 1.5368 0.05130 0.04365 -0.0735 0.0172 1.0000
13.000 1.5300 0.05508 0.04755 -0.0731 0.0166 1.0000
13.250 1.5276 0.05838 0.05102 -0.0728 0.0161 1.0000
13.500 1.5236 0.06196 0.05475 -0.0727 0.0156 1.0000
13.750 1.5182 0.06578 0.05872 -0.0728 0.0152 1.0000
14.000 1.5122 0.06980 0.06289 -0.0730 0.0149 1.0000
14.250 1.5056 0.07403 0.06726 -0.0734 0.0146 1.0000
14.500 1.4987 0.07841 0.07178 -0.0740 0.0143 1.0000
14.750 1.4917 0.08292 0.07644 -0.0748 0.0140 1.0000
15.000 1.4843 0.08756 0.08121 -0.0757 0.0137 1.0000
15.250 1.4768 0.09231 0.08608 -0.0767 0.0135 1.0000
15.500 1.4695 0.09710 0.09099 -0.0779 0.0133 1.0000
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Polar data table (+)
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