GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Reynolds number: 100,000 Max Cl/Cd: 48.16 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe217-il-100000-n5.txt Download as CSV file: xf-goe217-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 217 (MVA MK.12) 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2219 0.08830 0.08290 -0.0720 0.9572 0.0509
-10.500 -0.2938 0.06899 0.06319 -0.0901 0.9383 0.0489
-10.250 -0.3353 0.05791 0.05162 -0.1045 0.9149 0.0480
-10.000 -0.3409 0.05172 0.04501 -0.1147 0.8947 0.0477
-9.750 -0.3283 0.04727 0.04018 -0.1230 0.8765 0.0476
-9.500 -0.3079 0.04399 0.03658 -0.1288 0.8596 0.0476
-9.250 -0.2835 0.04139 0.03371 -0.1330 0.8442 0.0476
-9.000 -0.2571 0.03926 0.03132 -0.1360 0.8299 0.0478
-8.750 -0.2319 0.03753 0.02941 -0.1377 0.8138 0.0480
-8.500 -0.2058 0.03606 0.02778 -0.1389 0.7990 0.0484
-8.250 -0.1783 0.03469 0.02623 -0.1401 0.7855 0.0491
-8.000 -0.1515 0.03345 0.02483 -0.1411 0.7706 0.0497
-7.750 -0.1238 0.03232 0.02352 -0.1419 0.7572 0.0503
-7.500 -0.0964 0.03133 0.02236 -0.1422 0.7438 0.0508
-7.250 -0.0701 0.03051 0.02144 -0.1420 0.7305 0.0510
-7.000 -0.0439 0.02982 0.02062 -0.1414 0.7187 0.0513
-6.750 -0.0187 0.02925 0.02001 -0.1406 0.7063 0.0515
-6.500 0.0067 0.02880 0.01947 -0.1396 0.6957 0.0518
-6.250 0.0292 0.02851 0.01926 -0.1377 0.6842 0.0522
-6.000 0.0529 0.02828 0.01904 -0.1361 0.6738 0.0526
-5.750 0.0777 0.02806 0.01886 -0.1351 0.6632 0.0532
-5.500 0.1041 0.02782 0.01859 -0.1346 0.6531 0.0538
-5.250 0.1325 0.02751 0.01823 -0.1348 0.6442 0.0545
-5.000 0.1629 0.02707 0.01776 -0.1359 0.6347 0.0553
-4.750 0.1958 0.02653 0.01706 -0.1377 0.6269 0.0568
-4.500 0.2314 0.02573 0.01621 -0.1408 0.6185 0.0585
-4.250 0.2683 0.02492 0.01529 -0.1441 0.6100 0.0604
-4.000 0.3052 0.02425 0.01440 -0.1470 0.6031 0.0623
-3.750 0.3419 0.02359 0.01365 -0.1499 0.5951 0.0641
-3.500 0.3777 0.02305 0.01299 -0.1523 0.5878 0.0667
-3.250 0.4129 0.02261 0.01240 -0.1543 0.5820 0.0704
-3.000 0.4486 0.02214 0.01188 -0.1565 0.5760 0.0787
-2.750 0.4920 0.02089 0.01123 -0.1617 0.5696 0.2280
-2.500 0.5252 0.02073 0.01120 -0.1631 0.5641 0.2738
-2.250 0.5567 0.02079 0.01124 -0.1638 0.5593 0.3055
-2.000 0.5867 0.02096 0.01145 -0.1640 0.5540 0.3281
-1.750 0.6161 0.02118 0.01169 -0.1642 0.5484 0.3478
-1.500 0.6452 0.02146 0.01196 -0.1641 0.5434 0.3668
-1.250 0.6745 0.02176 0.01219 -0.1641 0.5393 0.3842
-1.000 0.7044 0.02212 0.01241 -0.1642 0.5359 0.4019
-0.750 0.7300 0.02268 0.01310 -0.1632 0.5315 0.4140
-0.500 0.7584 0.02304 0.01345 -0.1631 0.5272 0.4259
-0.250 0.7859 0.02336 0.01377 -0.1626 0.5231 0.4329
0.000 0.8177 0.02345 0.01370 -0.1635 0.5191 0.4437
0.250 0.8447 0.02379 0.01401 -0.1629 0.5157 0.4482
0.500 0.8725 0.02414 0.01433 -0.1626 0.5124 0.4546
0.750 0.9031 0.02433 0.01447 -0.1634 0.5085 0.4652
1.000 0.9288 0.02472 0.01494 -0.1628 0.5049 0.4691
1.250 0.9556 0.02507 0.01532 -0.1623 0.5015 0.4745
1.500 0.9846 0.02532 0.01551 -0.1625 0.4981 0.4823
1.750 1.0141 0.02556 0.01566 -0.1628 0.4950 0.4896
2.000 1.0413 0.02594 0.01601 -0.1623 0.4922 0.4945
2.250 1.0664 0.02638 0.01658 -0.1618 0.4888 0.5011
2.500 1.0947 0.02672 0.01692 -0.1622 0.4848 0.5105
2.750 1.1191 0.02707 0.01735 -0.1614 0.4803 0.5144
3.000 1.1456 0.02725 0.01751 -0.1609 0.4753 0.5192
3.250 1.1746 0.02736 0.01748 -0.1609 0.4703 0.5254
3.500 1.1989 0.02762 0.01782 -0.1607 0.4629 0.5324
3.750 1.2237 0.02777 0.01799 -0.1600 0.4566 0.5359
4.000 1.2503 0.02790 0.01808 -0.1596 0.4520 0.5397
4.250 1.2759 0.02819 0.01839 -0.1592 0.4478 0.5442
4.500 1.2988 0.02860 0.01890 -0.1586 0.4425 0.5492
4.750 1.3247 0.02888 0.01919 -0.1585 0.4375 0.5548
5.000 1.3503 0.02907 0.01939 -0.1581 0.4330 0.5585
5.250 1.3771 0.02923 0.01949 -0.1577 0.4292 0.5622
5.500 1.3961 0.02975 0.02019 -0.1565 0.4236 0.5660
5.750 1.4178 0.03013 0.02066 -0.1557 0.4180 0.5703
6.000 1.4424 0.03035 0.02086 -0.1553 0.4130 0.5752
6.250 1.4690 0.03050 0.02092 -0.1551 0.4085 0.5799
6.500 1.4835 0.03114 0.02180 -0.1532 0.4021 0.5830
6.750 1.5022 0.03154 0.02228 -0.1519 0.3960 0.5867
7.000 1.5249 0.03172 0.02243 -0.1511 0.3907 0.5909
7.250 1.5394 0.03235 0.02318 -0.1494 0.3840 0.5950
7.500 1.5541 0.03293 0.02383 -0.1477 0.3770 0.5998
7.750 1.5724 0.03319 0.02407 -0.1462 0.3712 0.6032
8.000 1.5767 0.03412 0.02519 -0.1431 0.3635 0.6065
8.250 1.5821 0.03483 0.02597 -0.1401 0.3564 0.6103
8.500 1.5901 0.03568 0.02688 -0.1377 0.3490 0.6143
8.750 1.5935 0.03695 0.02824 -0.1352 0.3402 0.6181
9.000 1.5989 0.03815 0.02947 -0.1330 0.3319 0.6216
9.250 1.5984 0.03987 0.03129 -0.1307 0.3224 0.6245
9.500 1.5982 0.04173 0.03321 -0.1287 0.3133 0.6279
9.750 1.5972 0.04381 0.03532 -0.1269 0.3038 0.6318
10.000 1.5933 0.04639 0.03796 -0.1253 0.2943 0.6356
10.250 1.5933 0.04867 0.04019 -0.1241 0.2857 0.6395
10.500 1.5859 0.05189 0.04348 -0.1229 0.2767 0.6420
10.750 1.5859 0.05430 0.04582 -0.1218 0.2693 0.6452
11.000 1.5786 0.05781 0.04941 -0.1210 0.2615 0.6481
11.250 1.5783 0.06044 0.05199 -0.1202 0.2551 0.6518
11.500 1.5756 0.06354 0.05512 -0.1196 0.2490 0.6556
11.750 1.5731 0.06661 0.05824 -0.1190 0.2433 0.6589
12.000 1.5783 0.06864 0.06020 -0.1182 0.2385 0.6630
12.250 1.5793 0.07141 0.06302 -0.1177 0.2340 0.6672
12.500 1.5779 0.07461 0.06629 -0.1175 0.2294 0.6715
12.750 1.5829 0.07686 0.06856 -0.1170 0.2254 0.6756
13.000 1.5968 0.07780 0.06940 -0.1161 0.2218 0.6805
13.250 1.5943 0.08125 0.07296 -0.1161 0.2179 0.6844
13.500 1.5918 0.08473 0.07655 -0.1162 0.2138 0.6884
13.750 1.5952 0.08730 0.07915 -0.1160 0.2101 0.6926
14.000 1.6095 0.08821 0.08000 -0.1153 0.2067 0.6987
14.250 1.6102 0.09125 0.08312 -0.1153 0.2034 0.7040
14.500 1.6034 0.09548 0.08753 -0.1159 0.2000 0.7081
14.750 1.6034 0.09870 0.09085 -0.1161 0.1969 0.7134
15.000 1.6097 0.10093 0.09312 -0.1161 0.1941 0.7199
15.250 1.6249 0.10173 0.09391 -0.1156 0.1917 0.7273
15.500 1.6280 0.10447 0.09673 -0.1158 0.1891 0.7339
15.750 1.6088 0.11085 0.10337 -0.1176 0.1859 0.7375
16.000 1.5992 0.11575 0.10845 -0.1190 0.1827 0.7429
16.250 1.6016 0.11869 0.11148 -0.1196 0.1799 0.7516
16.500 1.6154 0.11966 0.11251 -0.1194 0.1776 0.7674
16.750 1.6297 0.11952 0.11240 -0.1185 0.1756 0.9973
17.000 1.5685 0.13454 0.12789 -0.1253 0.1714 0.8015
17.250 1.5298 0.14500 0.13859 -0.1304 0.1668 0.8209
17.500 1.5494 0.14428 0.13784 -0.1298 0.1646 1.0000
17.750 1.5808 0.14203 0.13548 -0.1282 0.1630 1.0000
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