GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 100,000 Max Cl/Cd: 52.5 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe190-il-100000.txt Download as CSV file: xf-goe190-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3016 0.09954 0.09502 -0.0226 1.0000 0.1616
-7.250 -0.3334 0.09996 0.09560 -0.0207 1.0000 0.1665
-7.000 -0.3859 0.10179 0.09765 -0.0192 1.0000 0.1676
-6.750 -0.3555 0.09660 0.09244 -0.0151 1.0000 0.1703
-6.500 -0.3502 0.09489 0.09077 -0.0121 1.0000 0.1744
-6.250 -0.3682 0.09444 0.09041 -0.0089 1.0000 0.1775
-6.000 -0.3687 0.05614 0.05169 -0.0686 0.9866 0.1097
-5.750 -0.3042 0.03653 0.03008 -0.0980 0.9843 0.0957
-5.500 -0.2644 0.03329 0.02651 -0.1025 0.9777 0.0977
-5.250 -0.2207 0.03116 0.02404 -0.1067 0.9710 0.1001
-5.000 -0.1810 0.02935 0.02188 -0.1096 0.9625 0.1017
-4.750 -0.1355 0.02801 0.02021 -0.1132 0.9558 0.1057
-4.500 -0.0984 0.02699 0.01888 -0.1150 0.9457 0.1089
-4.250 -0.0541 0.02567 0.01770 -0.1180 0.9400 0.1134
-4.000 -0.0201 0.02490 0.01691 -0.1190 0.9286 0.1197
-3.750 0.0184 0.02408 0.01614 -0.1208 0.9191 0.1281
-3.500 0.0618 0.02324 0.01533 -0.1234 0.9108 0.1405
-3.250 0.0972 0.02229 0.01455 -0.1249 0.8993 0.1689
-3.000 0.1367 0.02274 0.01556 -0.1260 0.8878 0.2915
-2.750 0.1819 0.02456 0.01756 -0.1267 0.8796 0.3301
-2.500 0.2144 0.02554 0.01862 -0.1258 0.8667 0.3492
-2.250 0.2485 0.02619 0.01931 -0.1253 0.8551 0.3679
-2.000 0.2958 0.02612 0.01922 -0.1272 0.8499 0.3867
-1.750 0.3311 0.02605 0.01913 -0.1274 0.8381 0.4025
-1.500 0.3773 0.02569 0.01864 -0.1300 0.8295 0.4244
-1.250 0.4200 0.02510 0.01800 -0.1317 0.8195 0.4395
-1.000 0.4584 0.02435 0.01717 -0.1331 0.8066 0.4469
-0.750 0.5021 0.02362 0.01622 -0.1361 0.7939 0.4535
-0.500 0.5435 0.02298 0.01539 -0.1386 0.7810 0.4596
-0.250 0.5811 0.02256 0.01481 -0.1402 0.7679 0.4649
0.000 0.6122 0.02240 0.01446 -0.1410 0.7532 0.4703
0.250 0.6409 0.02225 0.01418 -0.1412 0.7395 0.4747
0.500 0.6700 0.02213 0.01397 -0.1414 0.7273 0.4785
0.750 0.7026 0.02204 0.01370 -0.1422 0.7164 0.4835
1.000 0.7277 0.02213 0.01367 -0.1419 0.7038 0.4882
1.250 0.7538 0.02207 0.01358 -0.1415 0.6930 0.4917
1.500 0.7831 0.02202 0.01344 -0.1416 0.6829 0.4957
1.750 0.8068 0.02214 0.01352 -0.1410 0.6715 0.5003
2.000 0.8357 0.02215 0.01343 -0.1410 0.6623 0.5054
2.250 0.8599 0.02219 0.01348 -0.1403 0.6518 0.5100
2.500 0.8858 0.02229 0.01354 -0.1399 0.6418 0.5147
2.750 0.9151 0.02233 0.01346 -0.1400 0.6326 0.5197
3.000 0.9378 0.02244 0.01365 -0.1391 0.6224 0.5245
3.250 0.9681 0.02247 0.01357 -0.1393 0.6143 0.5314
3.500 0.9901 0.02266 0.01382 -0.1382 0.6035 0.5372
3.750 1.0166 0.02277 0.01392 -0.1378 0.5945 0.5434
4.000 1.0431 0.02296 0.01409 -0.1375 0.5851 0.5500
4.250 1.0680 0.02319 0.01437 -0.1369 0.5756 0.5565
4.500 1.0983 0.02336 0.01445 -0.1372 0.5669 0.5656
4.750 1.1218 0.02370 0.01490 -0.1364 0.5564 0.5736
5.000 1.1520 0.02390 0.01501 -0.1366 0.5468 0.5835
5.250 1.1776 0.02410 0.01525 -0.1361 0.5352 0.5929
5.500 1.2021 0.02444 0.01568 -0.1355 0.5242 0.6035
5.750 1.2344 0.02465 0.01582 -0.1361 0.5154 0.6178
6.000 1.2542 0.02514 0.01654 -0.1348 0.5050 0.6324
6.250 1.2850 0.02538 0.01685 -0.1352 0.4968 0.6529
6.500 1.3040 0.02576 0.01756 -0.1337 0.4866 0.6819
6.750 1.3328 0.02582 0.01796 -0.1338 0.4779 1.0000
7.000 1.3544 0.02639 0.01859 -0.1328 0.4682 1.0000
7.250 1.3781 0.02698 0.01919 -0.1320 0.4595 1.0000
7.500 1.4013 0.02741 0.01964 -0.1310 0.4501 1.0000
7.750 1.4208 0.02798 0.02030 -0.1295 0.4404 1.0000
8.000 1.4487 0.02816 0.02039 -0.1292 0.4313 1.0000
8.250 1.4632 0.02862 0.02100 -0.1268 0.4196 1.0000
8.500 1.4830 0.02878 0.02118 -0.1251 0.4080 1.0000
8.750 1.5067 0.02874 0.02104 -0.1239 0.3966 1.0000
9.000 1.5231 0.02901 0.02139 -0.1217 0.3846 1.0000
9.250 1.5376 0.02945 0.02194 -0.1193 0.3727 1.0000
9.500 1.5552 0.02979 0.02229 -0.1174 0.3608 1.0000
9.750 1.5748 0.03010 0.02253 -0.1158 0.3486 1.0000
10.000 1.5894 0.03054 0.02301 -0.1134 0.3357 1.0000
10.250 1.5984 0.03121 0.02377 -0.1103 0.3227 1.0000
10.500 1.6080 0.03189 0.02452 -0.1073 0.3098 1.0000
10.750 1.6173 0.03256 0.02520 -0.1043 0.2970 1.0000
11.000 1.6256 0.03321 0.02582 -0.1012 0.2844 1.0000
11.250 1.6282 0.03392 0.02656 -0.0973 0.2721 1.0000
11.500 1.6235 0.03490 0.02767 -0.0925 0.2600 1.0000
11.750 1.6202 0.03595 0.02878 -0.0883 0.2479 1.0000
12.000 1.6165 0.03712 0.02996 -0.0844 0.2357 1.0000
12.250 1.6120 0.03848 0.03130 -0.0807 0.2235 1.0000
12.500 1.6050 0.04015 0.03300 -0.0772 0.2114 1.0000
12.750 1.5961 0.04225 0.03519 -0.0741 0.1996 1.0000
13.000 1.5886 0.04457 0.03753 -0.0714 0.1880 1.0000
13.250 1.5816 0.04708 0.04003 -0.0693 0.1771 1.0000
13.500 1.5765 0.04964 0.04247 -0.0675 0.1663 1.0000
13.750 1.5658 0.05290 0.04591 -0.0660 0.1565 1.0000
14.000 1.5578 0.05613 0.04917 -0.0648 0.1469 1.0000
14.250 1.5526 0.05915 0.05207 -0.0638 0.1376 1.0000
14.500 1.5393 0.06325 0.05640 -0.0634 0.1294 1.0000
14.750 1.5309 0.06696 0.06011 -0.0630 0.1213 1.0000
15.000 1.5206 0.07103 0.06423 -0.0630 0.1137 1.0000
15.250 1.5108 0.07530 0.06860 -0.0632 0.1062 1.0000
15.500 1.5062 0.07881 0.07194 -0.0632 0.0984 1.0000
15.750 1.4933 0.08389 0.07726 -0.0641 0.0925 1.0000
16.000 1.4924 0.08710 0.08032 -0.0639 0.0857 1.0000
16.250 1.4826 0.09197 0.08541 -0.0649 0.0808 1.0000
16.500 1.4896 0.09414 0.08740 -0.0640 0.0747 1.0000
16.750 1.4778 0.09950 0.09305 -0.0655 0.0718 1.0000
17.000 1.4748 0.10342 0.09706 -0.0663 0.0682 1.0000
17.250 1.4848 0.10532 0.09884 -0.0655 0.0641 1.0000
17.500 1.4723 0.11101 0.10483 -0.0676 0.0626 1.0000
17.750 1.4608 0.11668 0.11075 -0.0698 0.0611 1.0000
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