GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 100,000 Max Cl/Cd: 57.68 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe190-il-100000-n5.txt Download as CSV file: xf-goe190-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 190 (MVA MK.18) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3540 0.09416 0.08925 -0.0389 1.0000 0.0468
-8.750 -0.3669 0.08997 0.08514 -0.0391 1.0000 0.0469
-8.500 -0.3888 0.08499 0.08025 -0.0394 1.0000 0.0472
-8.250 -0.4213 0.07905 0.07441 -0.0399 0.9994 0.0474
-8.000 -0.4354 0.05342 0.04830 -0.0790 0.9831 0.0475
-7.750 -0.3995 0.04282 0.03694 -0.0995 0.9743 0.0487
-7.500 -0.3661 0.03942 0.03327 -0.1052 0.9680 0.0501
-7.250 -0.3308 0.03683 0.03043 -0.1100 0.9616 0.0524
-7.000 -0.2945 0.03391 0.02702 -0.1150 0.9552 0.0547
-6.750 -0.2599 0.03148 0.02411 -0.1184 0.9477 0.0562
-6.500 -0.2216 0.02952 0.02175 -0.1219 0.9435 0.0583
-6.250 -0.1970 0.02811 0.02035 -0.1219 0.9338 0.0602
-6.000 -0.1616 0.02681 0.01892 -0.1239 0.9288 0.0621
-5.750 -0.1358 0.02574 0.01774 -0.1238 0.9185 0.0637
-5.500 -0.1002 0.02472 0.01656 -0.1254 0.9130 0.0662
-5.250 -0.0746 0.02395 0.01565 -0.1250 0.9012 0.0686
-5.000 -0.0479 0.02309 0.01482 -0.1247 0.8907 0.0707
-4.750 -0.0151 0.02230 0.01406 -0.1255 0.8837 0.0731
-4.500 0.0116 0.02171 0.01345 -0.1252 0.8719 0.0758
-4.250 0.0412 0.02111 0.01275 -0.1255 0.8613 0.0800
-4.000 0.0758 0.02033 0.01190 -0.1267 0.8533 0.0850
-3.750 0.1090 0.01957 0.01106 -0.1278 0.8426 0.0910
-3.500 0.1447 0.01874 0.01016 -0.1295 0.8327 0.1009
-3.250 0.1853 0.01747 0.00912 -0.1325 0.8248 0.1542
-3.000 0.2225 0.01737 0.00934 -0.1339 0.8135 0.2536
-2.750 0.2633 0.01752 0.00929 -0.1358 0.8026 0.2896
-2.500 0.3053 0.01763 0.00919 -0.1379 0.7914 0.3087
-2.250 0.3414 0.01794 0.00943 -0.1388 0.7777 0.3218
-2.000 0.3768 0.01817 0.00957 -0.1397 0.7637 0.3325
-1.750 0.4115 0.01837 0.00961 -0.1405 0.7495 0.3452
-1.500 0.4444 0.01867 0.00983 -0.1409 0.7353 0.3558
-1.250 0.4771 0.01866 0.00963 -0.1416 0.7211 0.3625
-1.000 0.5061 0.01867 0.00953 -0.1415 0.7061 0.3661
-0.750 0.5340 0.01864 0.00938 -0.1413 0.6912 0.3704
-0.500 0.5619 0.01856 0.00913 -0.1412 0.6768 0.3749
-0.250 0.5893 0.01852 0.00895 -0.1410 0.6633 0.3787
0.000 0.6163 0.01855 0.00892 -0.1406 0.6508 0.3819
0.250 0.6431 0.01856 0.00885 -0.1402 0.6386 0.3854
0.500 0.6693 0.01855 0.00876 -0.1398 0.6265 0.3892
0.750 0.6965 0.01855 0.00861 -0.1396 0.6155 0.3936
1.000 0.7235 0.01859 0.00859 -0.1392 0.6056 0.3969
1.250 0.7493 0.01866 0.00865 -0.1387 0.5951 0.4004
1.500 0.7762 0.01874 0.00865 -0.1383 0.5859 0.4046
1.750 0.8027 0.01882 0.00864 -0.1379 0.5767 0.4089
2.000 0.8293 0.01892 0.00866 -0.1376 0.5683 0.4127
2.250 0.8553 0.01904 0.00879 -0.1371 0.5600 0.4162
2.500 0.8815 0.01920 0.00891 -0.1366 0.5521 0.4207
2.750 0.9075 0.01937 0.00902 -0.1362 0.5438 0.4261
3.000 0.9340 0.01955 0.00918 -0.1358 0.5364 0.4304
3.250 0.9596 0.01975 0.00941 -0.1353 0.5285 0.4345
3.500 0.9874 0.01998 0.00956 -0.1352 0.5217 0.4395
3.750 1.0125 0.02021 0.00984 -0.1346 0.5133 0.4451
4.000 1.0396 0.02045 0.01008 -0.1344 0.5062 0.4499
4.250 1.0651 0.02072 0.01039 -0.1339 0.4986 0.4559
4.500 1.0912 0.02098 0.01068 -0.1335 0.4911 0.4619
4.750 1.1172 0.02125 0.01098 -0.1331 0.4838 0.4674
5.000 1.1416 0.02152 0.01130 -0.1325 0.4752 0.4737
5.250 1.1665 0.02176 0.01159 -0.1319 0.4669 0.4800
5.500 1.1892 0.02199 0.01189 -0.1308 0.4566 0.4871
5.750 1.2118 0.02222 0.01219 -0.1298 0.4467 0.4942
6.000 1.2352 0.02244 0.01248 -0.1290 0.4380 0.5018
6.250 1.2578 0.02272 0.01288 -0.1280 0.4295 0.5095
6.500 1.2810 0.02297 0.01320 -0.1271 0.4217 0.5180
6.750 1.3029 0.02326 0.01365 -0.1261 0.4130 0.5271
7.000 1.3252 0.02353 0.01398 -0.1250 0.4051 0.5376
7.250 1.3463 0.02384 0.01447 -0.1239 0.3966 0.5484
7.500 1.3678 0.02412 0.01484 -0.1228 0.3890 0.5612
7.750 1.3876 0.02446 0.01539 -0.1214 0.3801 0.5775
8.000 1.4078 0.02471 0.01577 -0.1201 0.3723 0.6036
8.250 1.4265 0.02473 0.01632 -0.1186 0.3626 1.0000
8.500 1.4438 0.02520 0.01677 -0.1168 0.3533 1.0000
8.750 1.4587 0.02570 0.01732 -0.1146 0.3423 1.0000
9.000 1.4718 0.02625 0.01792 -0.1122 0.3305 1.0000
9.250 1.4834 0.02683 0.01850 -0.1095 0.3197 1.0000
9.500 1.4944 0.02746 0.01915 -0.1068 0.3093 1.0000
9.750 1.5052 0.02816 0.01995 -0.1042 0.2991 1.0000
10.000 1.5148 0.02891 0.02073 -0.1014 0.2893 1.0000
10.250 1.5233 0.02974 0.02164 -0.0987 0.2785 1.0000
10.500 1.5312 0.03064 0.02264 -0.0959 0.2681 1.0000
10.750 1.5374 0.03164 0.02367 -0.0931 0.2577 1.0000
11.000 1.5424 0.03275 0.02486 -0.0903 0.2467 1.0000
11.250 1.5468 0.03397 0.02620 -0.0877 0.2359 1.0000
11.500 1.5495 0.03536 0.02763 -0.0850 0.2254 1.0000
11.750 1.5501 0.03695 0.02925 -0.0824 0.2152 1.0000
12.000 1.5511 0.03867 0.03107 -0.0801 0.2048 1.0000
12.250 1.5500 0.04065 0.03310 -0.0779 0.1954 1.0000
12.500 1.5466 0.04293 0.03539 -0.0759 0.1863 1.0000
12.750 1.5437 0.04537 0.03793 -0.0743 0.1770 1.0000
13.000 1.5381 0.04819 0.04076 -0.0729 0.1686 1.0000
13.250 1.5319 0.05125 0.04392 -0.0718 0.1596 1.0000
13.500 1.5249 0.05457 0.04731 -0.0710 0.1510 1.0000
13.750 1.5156 0.05828 0.05106 -0.0705 0.1428 1.0000
14.000 1.5081 0.06203 0.05494 -0.0703 0.1344 1.0000
14.250 1.4970 0.06633 0.05924 -0.0705 0.1272 1.0000
14.500 1.4888 0.07054 0.06362 -0.0709 0.1189 1.0000
14.750 1.4781 0.07518 0.06830 -0.0716 0.1126 1.0000
15.000 1.4692 0.07975 0.07300 -0.0724 0.1059 1.0000
15.250 1.4581 0.08471 0.07799 -0.0734 0.1008 1.0000
15.500 1.4499 0.08941 0.08282 -0.0745 0.0952 1.0000
15.750 1.4389 0.09458 0.08803 -0.0759 0.0905 1.0000
16.000 1.4302 0.09951 0.09306 -0.0773 0.0859 1.0000
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