MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Reynolds number: 50,000 Max Cl/Cd: 15.75 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske5-il-50000.txt Download as CSV file: xf-marske5-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE MONARCH AIRFOIL (NACA 43012A)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4468 0.10823 0.10172 0.0210 1.0000 0.3287
-9.250 -0.4396 0.10533 0.09890 0.0221 1.0000 0.3508
-9.000 -0.4516 0.10363 0.09730 0.0229 1.0000 0.3734
-8.750 -0.4181 0.09924 0.09293 0.0250 1.0000 0.4012
-8.500 -0.4110 0.09649 0.09026 0.0268 1.0000 0.4302
-8.250 -0.4081 0.09440 0.08826 0.0290 1.0000 0.4621
-8.000 -0.3841 0.09110 0.08499 0.0311 1.0000 0.4981
-7.750 -0.3510 0.08755 0.08147 0.0327 1.0000 0.5398
-7.500 -0.3420 0.08572 0.07972 0.0355 1.0000 0.5828
-7.000 -0.2913 0.07831 0.07240 0.0358 1.0000 0.6423
-6.750 -0.2795 0.07582 0.06999 0.0368 1.0000 0.6688
-6.000 -0.5528 0.05299 0.04671 0.0125 1.0000 0.2597
-5.750 -0.5445 0.04813 0.04082 0.0131 1.0000 0.1936
-5.500 -0.5315 0.04495 0.03720 0.0155 1.0000 0.1756
-5.250 -0.5204 0.04281 0.03437 0.0188 1.0000 0.1630
-5.000 -0.5041 0.04002 0.03153 0.0207 1.0000 0.1594
-4.750 -0.4895 0.03771 0.02894 0.0232 1.0000 0.1538
-4.500 -0.4771 0.03664 0.02723 0.0268 1.0000 0.1475
-4.250 -0.4629 0.03497 0.02540 0.0292 1.0000 0.1466
-4.000 -0.4505 0.03370 0.02393 0.0317 1.0000 0.1471
-3.750 -0.4363 0.03219 0.02235 0.0337 1.0000 0.1480
-3.500 -0.4202 0.03093 0.02100 0.0354 1.0000 0.1488
-3.250 -0.4024 0.02986 0.01987 0.0368 1.0000 0.1495
-3.000 -0.3336 0.02818 0.01828 0.0294 0.9828 0.1581
-2.750 0.1272 0.02320 0.01513 -0.0260 0.6907 1.0000
-2.500 0.1440 0.02357 0.01482 -0.0234 0.6080 1.0000
-2.250 0.1636 0.02375 0.01447 -0.0217 0.5617 1.0000
-2.000 0.1850 0.02393 0.01420 -0.0205 0.5314 1.0000
-1.750 0.2075 0.02414 0.01410 -0.0196 0.5061 1.0000
-1.500 0.2302 0.02437 0.01406 -0.0188 0.4867 1.0000
-1.250 0.2525 0.02466 0.01412 -0.0180 0.4703 1.0000
-1.000 0.2745 0.02502 0.01428 -0.0170 0.4579 1.0000
-0.750 0.2969 0.02541 0.01447 -0.0162 0.4468 1.0000
-0.500 0.3201 0.02588 0.01487 -0.0157 0.4362 1.0000
-0.250 0.3423 0.02635 0.01510 -0.0147 0.4276 1.0000
0.000 0.3648 0.02691 0.01570 -0.0141 0.4183 1.0000
0.250 0.3867 0.02747 0.01608 -0.0132 0.4112 1.0000
0.500 0.4092 0.02824 0.01691 -0.0127 0.4055 1.0000
0.750 0.4313 0.02904 0.01775 -0.0121 0.3998 1.0000
1.000 0.4531 0.02979 0.01841 -0.0113 0.3949 1.0000
1.250 0.4744 0.03077 0.01942 -0.0106 0.3902 1.0000
1.500 0.4949 0.03189 0.02070 -0.0102 0.3851 1.0000
1.750 0.5150 0.03293 0.02178 -0.0094 0.3803 1.0000
2.000 0.5352 0.03399 0.02280 -0.0085 0.3770 1.0000
2.250 0.5548 0.03534 0.02415 -0.0077 0.3746 1.0000
2.500 0.5714 0.03729 0.02637 -0.0075 0.3728 1.0000
2.750 0.5863 0.03948 0.02880 -0.0073 0.3711 1.0000
3.000 0.5989 0.04188 0.03142 -0.0071 0.3693 1.0000
3.250 0.6089 0.04453 0.03426 -0.0068 0.3675 1.0000
3.500 0.6151 0.04771 0.03763 -0.0067 0.3673 1.0000
3.750 0.6164 0.05155 0.04165 -0.0068 0.3698 1.0000
4.000 0.6188 0.05508 0.04526 -0.0065 0.3728 1.0000
4.250 0.6242 0.05819 0.04841 -0.0058 0.3753 1.0000
4.500 0.3167 0.08102 0.07161 -0.0161 0.6054 1.0000
4.750 0.3152 0.08228 0.07278 -0.0136 0.5910 1.0000
5.000 0.3209 0.08412 0.07454 -0.0119 0.5781 1.0000
5.250 0.3519 0.08762 0.07800 -0.0126 0.5689 1.0000
5.500 0.3429 0.08827 0.07857 -0.0097 0.5548 1.0000
5.750 0.3454 0.09013 0.08035 -0.0081 0.5434 1.0000
6.000 0.3772 0.09381 0.08401 -0.0086 0.5337 1.0000
6.250 0.3693 0.09451 0.08463 -0.0062 0.5191 1.0000
6.500 0.3709 0.09627 0.08633 -0.0047 0.5065 1.0000
6.750 0.4065 0.10058 0.09062 -0.0054 0.4981 1.0000
7.000 0.3920 0.10081 0.09078 -0.0030 0.4846 1.0000
7.250 0.3969 0.10310 0.09302 -0.0021 0.4751 1.0000
7.500 0.4212 0.10631 0.09623 -0.0018 0.4639 1.0000
7.750 0.4121 0.10728 0.09714 -0.0003 0.4514 1.0000
8.000 0.4530 0.11274 0.10261 -0.0010 0.4449 1.0000
8.250 0.4297 0.11205 0.10185 0.0009 0.4322 1.0000
8.500 0.4506 0.11609 0.10587 0.0009 0.4263 1.0000
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Polar data table (+)
Polar graphs
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