GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.59 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe190-il-1000000-n5.txt Download as CSV file: xf-goe190-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6847 0.08797 0.08556 -0.0752 0.9931 0.0119
-15.500 -0.7213 0.07790 0.07534 -0.0821 0.9918 0.0118
-15.250 -0.7426 0.07044 0.06777 -0.0877 0.9903 0.0119
-15.000 -0.7539 0.06449 0.06171 -0.0927 0.9888 0.0121
-14.750 -0.7609 0.05922 0.05635 -0.0975 0.9873 0.0122
-14.500 -0.7620 0.05461 0.05165 -0.1023 0.9859 0.0124
-14.250 -0.7607 0.05012 0.04707 -0.1076 0.9845 0.0126
-14.000 -0.7592 0.04627 0.04315 -0.1118 0.9823 0.0128
-13.750 -0.7648 0.04280 0.03960 -0.1145 0.9783 0.0129
-13.500 -0.7588 0.03836 0.03508 -0.1213 0.9753 0.0133
-13.250 -0.7404 0.03429 0.03091 -0.1295 0.9736 0.0137
-13.000 -0.7155 0.03066 0.02720 -0.1376 0.9724 0.0143
-12.750 -0.6966 0.02777 0.02422 -0.1426 0.9700 0.0149
-12.500 -0.6778 0.02539 0.02174 -0.1460 0.9670 0.0154
-12.250 -0.6528 0.02330 0.01954 -0.1497 0.9649 0.0159
-12.000 -0.6248 0.02141 0.01758 -0.1531 0.9629 0.0168
-11.750 -0.5959 0.01993 0.01604 -0.1559 0.9613 0.0177
-11.500 -0.5670 0.01868 0.01472 -0.1580 0.9600 0.0185
-11.250 -0.5372 0.01755 0.01349 -0.1600 0.9588 0.0192
-11.000 -0.5129 0.01656 0.01243 -0.1606 0.9566 0.0199
-10.750 -0.4895 0.01575 0.01158 -0.1607 0.9534 0.0205
-10.500 -0.4631 0.01513 0.01092 -0.1611 0.9506 0.0213
-10.250 -0.4355 0.01462 0.01036 -0.1615 0.9483 0.0221
-10.000 -0.4071 0.01413 0.00980 -0.1620 0.9462 0.0229
-9.750 -0.3771 0.01369 0.00930 -0.1627 0.9442 0.0234
-9.500 -0.3523 0.01317 0.00873 -0.1624 0.9413 0.0242
-9.250 -0.3286 0.01276 0.00830 -0.1618 0.9373 0.0248
-9.000 -0.3023 0.01240 0.00790 -0.1616 0.9332 0.0255
-8.750 -0.2733 0.01207 0.00753 -0.1619 0.9296 0.0263
-8.500 -0.2475 0.01175 0.00717 -0.1615 0.9243 0.0270
-8.250 -0.2216 0.01143 0.00681 -0.1611 0.9157 0.0276
-8.000 -0.1943 0.01115 0.00645 -0.1609 0.9025 0.0281
-7.750 -0.1650 0.01086 0.00578 -0.1611 0.8169 0.0289
-7.500 -0.1442 0.01083 0.00552 -0.1595 0.7732 0.0297
-7.250 -0.1200 0.01072 0.00528 -0.1587 0.7526 0.0305
-7.000 -0.0950 0.01057 0.00504 -0.1581 0.7378 0.0311
-6.750 -0.0688 0.01041 0.00481 -0.1577 0.7277 0.0319
-6.500 -0.0426 0.01025 0.00457 -0.1572 0.7193 0.0325
-6.250 -0.0161 0.01008 0.00432 -0.1568 0.7108 0.0330
-6.000 0.0103 0.00993 0.00410 -0.1564 0.7027 0.0334
-5.750 0.0368 0.00971 0.00382 -0.1560 0.6940 0.0344
-5.500 0.0631 0.00954 0.00359 -0.1556 0.6861 0.0356
-5.250 0.0901 0.00939 0.00341 -0.1553 0.6776 0.0365
-5.000 0.1166 0.00928 0.00323 -0.1548 0.6678 0.0375
-4.750 0.1431 0.00918 0.00307 -0.1543 0.6552 0.0384
-4.500 0.1693 0.00911 0.00291 -0.1538 0.6391 0.0393
-4.250 0.1944 0.00910 0.00278 -0.1530 0.6097 0.0400
-4.000 0.2176 0.00916 0.00262 -0.1520 0.5674 0.0420
-3.750 0.2426 0.00919 0.00254 -0.1512 0.5427 0.0441
-3.500 0.2689 0.00917 0.00244 -0.1507 0.5302 0.0458
-3.250 0.2956 0.00916 0.00236 -0.1503 0.5215 0.0474
-3.000 0.3227 0.00909 0.00226 -0.1499 0.5155 0.0500
-2.750 0.3496 0.00904 0.00218 -0.1495 0.5094 0.0532
-2.500 0.3765 0.00901 0.00211 -0.1491 0.5041 0.0564
-2.250 0.4039 0.00895 0.00204 -0.1488 0.4995 0.0611
-2.000 0.4310 0.00888 0.00197 -0.1485 0.4952 0.0689
-1.750 0.4568 0.00848 0.00178 -0.1481 0.4911 0.1504
-1.500 0.4827 0.00822 0.00169 -0.1477 0.4870 0.2189
-1.250 0.5101 0.00817 0.00170 -0.1474 0.4833 0.2417
-1.000 0.5374 0.00817 0.00171 -0.1471 0.4790 0.2550
-0.750 0.5645 0.00820 0.00173 -0.1467 0.4748 0.2642
-0.500 0.5915 0.00824 0.00177 -0.1463 0.4709 0.2739
-0.250 0.6188 0.00826 0.00180 -0.1460 0.4677 0.2814
0.000 0.6462 0.00829 0.00183 -0.1457 0.4638 0.2866
0.250 0.6733 0.00834 0.00186 -0.1453 0.4590 0.2909
0.500 0.7000 0.00839 0.00190 -0.1449 0.4542 0.2952
0.750 0.7270 0.00843 0.00195 -0.1445 0.4504 0.3002
1.000 0.7542 0.00847 0.00199 -0.1442 0.4462 0.3044
1.250 0.7810 0.00853 0.00203 -0.1437 0.4412 0.3069
1.500 0.8074 0.00861 0.00208 -0.1433 0.4352 0.3084
1.750 0.8342 0.00865 0.00213 -0.1429 0.4290 0.3112
2.000 0.8601 0.00874 0.00219 -0.1423 0.4201 0.3139
2.250 0.8865 0.00881 0.00226 -0.1418 0.4113 0.3167
2.500 0.9123 0.00892 0.00233 -0.1413 0.4016 0.3196
2.750 0.9381 0.00903 0.00241 -0.1407 0.3917 0.3226
3.000 0.9637 0.00915 0.00250 -0.1401 0.3825 0.3250
3.500 1.0139 0.00943 0.00272 -0.1388 0.3603 0.3313
3.750 1.0389 0.00957 0.00285 -0.1381 0.3512 0.3348
4.000 1.0637 0.00973 0.00298 -0.1374 0.3421 0.3380
4.250 1.0887 0.00986 0.00311 -0.1367 0.3352 0.3410
4.500 1.1134 0.01001 0.00324 -0.1360 0.3276 0.3439
4.750 1.1379 0.01016 0.00340 -0.1352 0.3204 0.3480
5.000 1.1625 0.01031 0.00355 -0.1345 0.3138 0.3521
5.250 1.1864 0.01050 0.00372 -0.1336 0.3056 0.3566
5.750 1.2341 0.01084 0.00407 -0.1319 0.2919 0.3652
6.000 1.2581 0.01098 0.00424 -0.1311 0.2855 0.3698
6.250 1.2807 0.01122 0.00445 -0.1300 0.2759 0.3742
6.500 1.3040 0.01138 0.00462 -0.1291 0.2689 0.3781
6.750 1.3253 0.01162 0.00485 -0.1278 0.2596 0.3829
7.000 1.3464 0.01185 0.00506 -0.1264 0.2483 0.3879
7.250 1.3667 0.01210 0.00529 -0.1249 0.2373 0.3929
7.500 1.3855 0.01244 0.00559 -0.1232 0.2214 0.3978
7.750 1.4036 0.01281 0.00591 -0.1214 0.2058 0.4032
8.000 1.4209 0.01322 0.00626 -0.1194 0.1906 0.4082
8.250 1.4373 0.01369 0.00666 -0.1173 0.1751 0.4122
8.500 1.4540 0.01411 0.00705 -0.1154 0.1636 0.4171
8.750 1.4702 0.01456 0.00747 -0.1133 0.1525 0.4222
9.000 1.4855 0.01505 0.00791 -0.1111 0.1405 0.4266
9.250 1.5028 0.01542 0.00830 -0.1093 0.1327 0.4318
9.500 1.5187 0.01586 0.00873 -0.1072 0.1246 0.4374
9.750 1.5321 0.01644 0.00925 -0.1049 0.1111 0.4427
10.000 1.5424 0.01716 0.00989 -0.1020 0.0946 0.4469
10.250 1.5518 0.01793 0.01060 -0.0992 0.0811 0.4514
10.500 1.5641 0.01854 0.01121 -0.0968 0.0742 0.4565
11.000 1.5873 0.01988 0.01256 -0.0920 0.0617 0.4672
11.250 1.5974 0.02064 0.01333 -0.0895 0.0563 0.4726
11.500 1.6089 0.02134 0.01405 -0.0872 0.0521 0.4783
11.750 1.6174 0.02222 0.01494 -0.0847 0.0470 0.4839
12.000 1.6252 0.02317 0.01590 -0.0822 0.0416 0.4897
12.250 1.6306 0.02429 0.01704 -0.0795 0.0356 0.4959
12.500 1.6371 0.02540 0.01818 -0.0771 0.0319 0.5034
12.750 1.6404 0.02678 0.01957 -0.0746 0.0268 0.5122
13.250 1.6441 0.02998 0.02286 -0.0700 0.0185 0.5400
13.500 1.6461 0.03162 0.02468 -0.0680 0.0162 0.6181
14.000 1.7044 0.03617 0.02987 -0.0766 0.0122 1.0000
14.250 1.7081 0.03825 0.03202 -0.0756 0.0115 1.0000
14.500 1.7105 0.04052 0.03436 -0.0747 0.0110 1.0000
14.750 1.7107 0.04310 0.03700 -0.0738 0.0104 1.0000
15.000 1.7103 0.04581 0.03979 -0.0731 0.0099 1.0000
15.250 1.7097 0.04860 0.04265 -0.0725 0.0096 1.0000
15.500 1.7091 0.05144 0.04559 -0.0720 0.0093 1.0000
15.750 1.7072 0.05452 0.04876 -0.0717 0.0090 1.0000
16.000 1.7043 0.05782 0.05214 -0.0715 0.0088 1.0000
16.250 1.6999 0.06137 0.05577 -0.0715 0.0086 1.0000
16.500 1.6948 0.06507 0.05956 -0.0715 0.0083 1.0000
16.750 1.6886 0.06899 0.06357 -0.0718 0.0081 1.0000
17.000 1.6811 0.07313 0.06779 -0.0721 0.0078 1.0000
17.250 1.6731 0.07734 0.07210 -0.0726 0.0077 1.0000
17.500 1.6637 0.08181 0.07665 -0.0731 0.0075 1.0000
17.750 1.6566 0.08600 0.08093 -0.0737 0.0074 1.0000
18.000 1.6487 0.09034 0.08537 -0.0744 0.0073 1.0000
18.250 1.6401 0.09483 0.08995 -0.0752 0.0072 1.0000
18.500 1.6312 0.09944 0.09467 -0.0762 0.0070 1.0000
18.750 1.6226 0.10409 0.09941 -0.0773 0.0069 1.0000
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Polar data table (+)
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