GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 200,000 Max Cl/Cd: 77.3 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe190-il-200000.txt Download as CSV file: xf-goe190-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2566 0.09965 0.09657 -0.0284 1.0000 0.0750
-8.750 -0.2634 0.09748 0.09444 -0.0275 1.0000 0.0778
-8.500 -0.2909 0.08977 0.08678 -0.0400 0.9949 0.0817
-8.250 -0.2515 0.08626 0.08323 -0.0373 0.9936 0.0842
-8.000 -0.2277 0.08326 0.08022 -0.0392 0.9893 0.0873
-7.750 -0.3844 0.08962 0.08655 -0.0321 0.9975 0.0828
-7.500 -0.3470 0.08810 0.08498 -0.0313 0.9957 0.0850
-7.250 -0.3484 0.03696 0.03207 -0.1094 0.9719 0.0592
-7.000 -0.3119 0.03353 0.02857 -0.1138 0.9693 0.0611
-6.750 -0.2803 0.03036 0.02498 -0.1170 0.9611 0.0615
-6.500 -0.2408 0.02795 0.02223 -0.1208 0.9572 0.0625
-6.250 -0.2039 0.02627 0.02032 -0.1233 0.9519 0.0647
-6.000 -0.1693 0.02467 0.01841 -0.1252 0.9449 0.0662
-5.750 -0.1286 0.02323 0.01669 -0.1278 0.9414 0.0676
-5.500 -0.0960 0.02254 0.01575 -0.1287 0.9334 0.0693
-5.250 -0.0614 0.02050 0.01365 -0.1303 0.9283 0.0715
-5.000 -0.0212 0.01932 0.01248 -0.1326 0.9252 0.0737
-4.750 0.0065 0.01850 0.01163 -0.1323 0.9148 0.0764
-4.500 0.0465 0.01764 0.01072 -0.1344 0.9107 0.0799
-4.250 0.0749 0.01691 0.00995 -0.1341 0.9003 0.0822
-4.000 0.1127 0.01585 0.00897 -0.1358 0.8956 0.0870
-3.750 0.1416 0.01521 0.00830 -0.1357 0.8847 0.0928
-3.500 0.1813 0.01431 0.00741 -0.1376 0.8796 0.1024
-3.000 0.2502 0.01292 0.00657 -0.1398 0.8567 0.2798
-2.750 0.2959 0.01320 0.00676 -0.1424 0.8466 0.3094
-2.500 0.3414 0.01344 0.00694 -0.1451 0.8335 0.3262
-2.250 0.3848 0.01362 0.00700 -0.1474 0.8161 0.3384
-2.000 0.4221 0.01395 0.00729 -0.1486 0.7952 0.3474
-1.750 0.4556 0.01411 0.00718 -0.1493 0.7742 0.3565
-1.500 0.4848 0.01444 0.00748 -0.1490 0.7546 0.3625
-1.250 0.5126 0.01477 0.00766 -0.1485 0.7364 0.3710
-1.000 0.5388 0.01500 0.00781 -0.1478 0.7192 0.3779
-0.750 0.5644 0.01527 0.00802 -0.1469 0.7032 0.3839
-0.500 0.5907 0.01525 0.00782 -0.1465 0.6882 0.3897
-0.250 0.6165 0.01521 0.00767 -0.1459 0.6748 0.3930
0.000 0.6426 0.01525 0.00764 -0.1453 0.6628 0.3961
0.250 0.6681 0.01523 0.00756 -0.1447 0.6504 0.3993
0.500 0.6939 0.01520 0.00744 -0.1441 0.6387 0.4031
0.750 0.7208 0.01520 0.00727 -0.1438 0.6287 0.4078
1.000 0.7462 0.01516 0.00722 -0.1431 0.6184 0.4105
1.250 0.7721 0.01518 0.00721 -0.1426 0.6088 0.4136
1.500 0.7985 0.01523 0.00717 -0.1421 0.5997 0.4171
1.750 0.8244 0.01527 0.00716 -0.1416 0.5901 0.4212
2.000 0.8517 0.01536 0.00711 -0.1413 0.5821 0.4255
2.250 0.8768 0.01542 0.00723 -0.1407 0.5732 0.4289
2.500 0.9043 0.01559 0.00729 -0.1405 0.5655 0.4330
2.750 0.9294 0.01568 0.00740 -0.1398 0.5563 0.4374
3.000 0.9572 0.01587 0.00747 -0.1397 0.5485 0.4418
3.250 0.9818 0.01598 0.00765 -0.1389 0.5398 0.4454
3.500 1.0096 0.01623 0.00782 -0.1388 0.5324 0.4505
3.750 1.0338 0.01640 0.00802 -0.1380 0.5234 0.4563
4.250 1.0836 0.01673 0.00839 -0.1367 0.5050 0.4660
4.500 1.1098 0.01699 0.00855 -0.1362 0.4963 0.4721
4.750 1.1324 0.01706 0.00874 -0.1351 0.4866 0.4768
5.000 1.1580 0.01729 0.00895 -0.1346 0.4787 0.4831
5.250 1.1811 0.01742 0.00916 -0.1336 0.4700 0.4897
5.500 1.2067 0.01762 0.00936 -0.1331 0.4626 0.4966
5.750 1.2288 0.01775 0.00959 -0.1319 0.4537 0.5042
6.000 1.2548 0.01794 0.00977 -0.1315 0.4469 0.5113
6.250 1.2763 0.01808 0.01006 -0.1302 0.4383 0.5193
6.500 1.3006 0.01822 0.01023 -0.1294 0.4312 0.5273
6.750 1.3216 0.01837 0.01052 -0.1281 0.4226 0.5367
7.000 1.3456 0.01852 0.01068 -0.1273 0.4148 0.5473
7.250 1.3670 0.01865 0.01098 -0.1261 0.4052 0.5580
7.500 1.3902 0.01880 0.01116 -0.1252 0.3963 0.5705
7.750 1.4104 0.01891 0.01139 -0.1237 0.3857 0.5848
8.000 1.4307 0.01907 0.01169 -0.1223 0.3751 0.6053
8.250 1.4609 0.01890 0.01202 -0.1232 0.3640 1.0000
8.500 1.4793 0.01924 0.01239 -0.1214 0.3537 1.0000
8.750 1.4971 0.01964 0.01281 -0.1196 0.3434 1.0000
9.000 1.5145 0.02010 0.01321 -0.1177 0.3332 1.0000
9.250 1.5292 0.02051 0.01368 -0.1154 0.3221 1.0000
9.500 1.5422 0.02097 0.01418 -0.1127 0.3109 1.0000
9.750 1.5542 0.02151 0.01469 -0.1100 0.3001 1.0000
10.000 1.5640 0.02205 0.01525 -0.1069 0.2881 1.0000
10.250 1.5729 0.02261 0.01587 -0.1038 0.2748 1.0000
10.500 1.5806 0.02325 0.01654 -0.1006 0.2608 1.0000
10.750 1.5871 0.02400 0.01729 -0.0974 0.2460 1.0000
11.000 1.5929 0.02486 0.01815 -0.0943 0.2313 1.0000
11.250 1.5980 0.02585 0.01915 -0.0913 0.2168 1.0000
11.500 1.6023 0.02699 0.02028 -0.0883 0.2036 1.0000
11.750 1.6048 0.02830 0.02158 -0.0854 0.1911 1.0000
12.000 1.6052 0.02985 0.02310 -0.0825 0.1794 1.0000
12.250 1.6048 0.03157 0.02482 -0.0797 0.1680 1.0000
12.500 1.6053 0.03336 0.02665 -0.0774 0.1567 1.0000
12.750 1.6040 0.03541 0.02874 -0.0752 0.1463 1.0000
13.000 1.6000 0.03782 0.03117 -0.0732 0.1366 1.0000
13.250 1.5973 0.04031 0.03370 -0.0716 0.1260 1.0000
13.500 1.5948 0.04293 0.03638 -0.0703 0.1160 1.0000
13.750 1.5893 0.04598 0.03947 -0.0693 0.1073 1.0000
14.000 1.5807 0.04952 0.04300 -0.0685 0.0995 1.0000
14.250 1.5743 0.05297 0.04652 -0.0679 0.0915 1.0000
14.500 1.5627 0.05717 0.05074 -0.0676 0.0852 1.0000
14.750 1.5532 0.06131 0.05494 -0.0676 0.0787 1.0000
15.000 1.5406 0.06599 0.05966 -0.0678 0.0734 1.0000
15.250 1.5299 0.07060 0.06435 -0.0683 0.0678 1.0000
15.500 1.5162 0.07570 0.06948 -0.0690 0.0631 1.0000
15.750 1.5064 0.08043 0.07430 -0.0698 0.0583 1.0000
16.000 1.4931 0.08564 0.07948 -0.0707 0.0550 1.0000
16.250 1.4866 0.09010 0.08409 -0.0716 0.0511 1.0000
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Polar data table (+)
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