GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 100,000 Max Cl/Cd: 54.7 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe234-il-100000.txt Download as CSV file: xf-goe234-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1498 0.12283 0.11823 -0.0575 0.9613 0.1227
-8.500 -0.1447 0.12164 0.11704 -0.0636 0.9555 0.1300
-8.250 -0.1465 0.11932 0.11476 -0.0653 0.9471 0.1318
-8.000 -0.1093 0.11424 0.10962 -0.0658 0.9441 0.1362
-7.750 -0.1055 0.11383 0.10921 -0.0726 0.9383 0.1451
-7.500 -0.1146 0.11206 0.10750 -0.0713 0.9271 0.1467
-7.250 -0.0687 0.10638 0.10175 -0.0727 0.9256 0.1520
-7.000 -0.0639 0.10495 0.10032 -0.0740 0.9178 0.1585
-6.750 -0.0797 0.10480 0.10024 -0.0775 0.9071 0.1622
-6.500 -0.0340 0.09911 0.09447 -0.0787 0.9064 0.1665
-6.250 -0.0400 0.09844 0.09384 -0.0754 0.8949 0.1702
-5.750 -0.0327 0.09470 0.09014 -0.0782 0.8778 0.1797
-5.500 0.1585 0.03930 0.03268 -0.2015 0.8776 0.1032
-5.250 0.2201 0.03641 0.02943 -0.2099 0.8755 0.1049
-5.000 0.2676 0.03513 0.02815 -0.2133 0.8733 0.1081
-4.750 0.2854 0.03514 0.02813 -0.2124 0.8632 0.1116
-4.500 0.3316 0.03425 0.02704 -0.2157 0.8596 0.1168
-4.250 0.3690 0.03415 0.02715 -0.2155 0.8568 0.1225
-4.000 0.3845 0.03463 0.02762 -0.2138 0.8463 0.1283
-3.750 0.4284 0.03419 0.02725 -0.2166 0.8426 0.1432
-3.500 0.4777 0.03378 0.02723 -0.2199 0.8403 0.1785
-3.250 0.4714 0.03596 0.02980 -0.2124 0.8282 0.1971
-3.000 0.4958 0.03802 0.03188 -0.2085 0.8237 0.2511
-2.750 0.4938 0.04037 0.03423 -0.2022 0.8129 0.2652
-2.500 0.5050 0.04239 0.03627 -0.1959 0.8071 0.2778
-2.250 0.5351 0.04361 0.03741 -0.1933 0.8046 0.2982
-1.750 0.5435 0.04625 0.04009 -0.1827 0.7880 0.3188
-1.500 0.5799 0.04651 0.04028 -0.1821 0.7863 0.3472
-0.750 0.6044 0.04835 0.04221 -0.1686 0.7659 0.4279
-0.500 0.5942 0.04950 0.04342 -0.1636 0.7534 0.4355
-0.250 0.6451 0.04795 0.04176 -0.1677 0.7518 0.4603
0.000 0.6958 0.04611 0.03983 -0.1714 0.7508 0.4800
0.250 0.7562 0.04474 0.03831 -0.1780 0.7494 0.5050
0.500 0.7384 0.04631 0.03998 -0.1723 0.7350 0.5085
0.750 0.7398 0.04799 0.04168 -0.1704 0.7227 0.5218
1.000 0.7821 0.04624 0.03988 -0.1724 0.7198 0.5415
1.250 0.8366 0.04393 0.03751 -0.1760 0.7185 0.5727
1.500 0.8898 0.04088 0.03440 -0.1783 0.7172 0.6188
1.750 0.8914 0.04136 0.03494 -0.1746 0.7047 0.6496
2.000 0.9403 0.03812 0.03167 -0.1758 0.7024 0.6912
2.250 0.9918 0.03529 0.02877 -0.1782 0.7001 0.7281
2.500 1.0036 0.03576 0.02930 -0.1765 0.6893 0.7467
2.750 1.0542 0.03420 0.02767 -0.1801 0.6855 0.7676
3.000 1.1066 0.03231 0.02573 -0.1839 0.6827 0.7788
3.250 1.1281 0.03306 0.02652 -0.1843 0.6722 0.7813
3.500 1.1849 0.03190 0.02528 -0.1897 0.6677 0.7743
3.750 1.2632 0.03109 0.02426 -0.1997 0.6641 0.7300
4.000 1.2928 0.03227 0.02546 -0.2022 0.6523 0.6907
4.250 1.3675 0.03152 0.02445 -0.2114 0.6473 0.6239
4.500 1.3943 0.03229 0.02522 -0.2126 0.6354 0.5888
4.750 1.4471 0.03147 0.02422 -0.2170 0.6287 0.5629
5.000 1.4728 0.03185 0.02462 -0.2171 0.6169 0.5514
5.250 1.5035 0.03154 0.02430 -0.2176 0.6072 0.5465
5.500 1.5402 0.03115 0.02383 -0.2191 0.5972 0.5383
5.750 1.5635 0.03144 0.02416 -0.2185 0.5849 0.5332
6.000 1.5973 0.03109 0.02374 -0.2193 0.5743 0.5307
6.250 1.6259 0.03097 0.02360 -0.2194 0.5619 0.5294
6.500 1.6460 0.03125 0.02394 -0.2181 0.5479 0.5296
6.750 1.6693 0.03142 0.02410 -0.2172 0.5341 0.5303
7.000 1.6952 0.03151 0.02414 -0.2168 0.5204 0.5308
7.250 1.7233 0.03155 0.02409 -0.2167 0.5067 0.5308
7.500 1.7439 0.03188 0.02440 -0.2154 0.4921 0.5309
7.750 1.7597 0.03241 0.02494 -0.2135 0.4773 0.5313
8.000 1.7757 0.03296 0.02548 -0.2115 0.4632 0.5322
8.250 1.7937 0.03349 0.02598 -0.2099 0.4504 0.5342
8.500 1.8163 0.03382 0.02619 -0.2090 0.4384 0.5370
8.750 1.8270 0.03456 0.02699 -0.2064 0.4266 0.5394
9.000 1.8401 0.03534 0.02780 -0.2041 0.4162 0.5416
9.250 1.8643 0.03576 0.02811 -0.2036 0.4065 0.5440
9.500 1.8671 0.03688 0.02939 -0.1998 0.3977 0.5453
9.750 1.8967 0.03732 0.02967 -0.2002 0.3894 0.5482
10.000 1.8925 0.03861 0.03118 -0.1954 0.3820 0.5496
10.250 1.9146 0.03904 0.03151 -0.1945 0.3731 0.5534
10.500 1.9103 0.04047 0.03313 -0.1901 0.3653 0.5559
10.750 1.9292 0.04100 0.03357 -0.1888 0.3566 0.5604
11.000 1.9265 0.04259 0.03536 -0.1849 0.3497 0.5629
11.250 1.9378 0.04350 0.03627 -0.1828 0.3418 0.5661
11.500 1.9393 0.04494 0.03785 -0.1796 0.3344 0.5685
11.750 1.9412 0.04623 0.03920 -0.1766 0.3258 0.5711
12.000 1.9405 0.04786 0.04093 -0.1735 0.3179 0.5738
12.250 1.9392 0.04952 0.04270 -0.1704 0.3099 0.5768
12.500 1.9387 0.05128 0.04454 -0.1677 0.3020 0.5804
12.750 1.9310 0.05351 0.04690 -0.1645 0.2934 0.5834
13.000 1.9246 0.05579 0.04931 -0.1617 0.2848 0.5870
13.250 1.9149 0.05842 0.05207 -0.1589 0.2757 0.5903
13.500 1.9043 0.06140 0.05522 -0.1564 0.2672 0.5936
13.750 1.8950 0.06430 0.05818 -0.1541 0.2574 0.5970
14.000 1.8781 0.06847 0.06260 -0.1522 0.2482 0.5993
14.250 1.8641 0.07244 0.06667 -0.1506 0.2370 0.6022
14.500 1.8462 0.07722 0.07158 -0.1494 0.2246 0.6046
14.750 1.8248 0.08300 0.07757 -0.1489 0.2107 0.6064
15.000 1.8012 0.08943 0.08413 -0.1488 0.1935 0.6080
15.250 1.7753 0.09670 0.09158 -0.1494 0.1683 0.6091
15.500 1.7459 0.10446 0.09918 -0.1504 0.1376 0.6097
15.750 1.7160 0.11251 0.10704 -0.1517 0.1211 0.6100
|
Polar data table (+)
Polar graphs
<< Back to GOE 234 (MVA CA5) AIRFOIL (goe234-il)