MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.31 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh32-il-1000000-n5.txt Download as CSV file: xf-mh32-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4093 0.04390 0.04204 -0.0665 0.9541 0.0024
-7.000 -0.4060 0.03667 0.03449 -0.0679 0.9371 0.0023
-6.750 -0.4048 0.02843 0.02574 -0.0674 0.9234 0.0022
-6.500 -0.3973 0.02164 0.01828 -0.0658 0.9131 0.0020
-6.250 -0.3806 0.01762 0.01368 -0.0644 0.9049 0.0019
-6.000 -0.3595 0.01506 0.01068 -0.0634 0.8983 0.0019
-5.750 -0.3360 0.01339 0.00870 -0.0626 0.8915 0.0018
-5.500 -0.3116 0.01214 0.00720 -0.0619 0.8854 0.0018
-5.250 -0.2865 0.01116 0.00603 -0.0613 0.8786 0.0018
-5.000 -0.2609 0.01041 0.00512 -0.0608 0.8721 0.0018
-4.750 -0.2348 0.00980 0.00439 -0.0604 0.8648 0.0018
-4.500 -0.2084 0.00931 0.00378 -0.0601 0.8576 0.0019
-4.250 -0.1817 0.00888 0.00322 -0.0598 0.8493 0.0020
-4.000 -0.1547 0.00854 0.00279 -0.0595 0.8412 0.0021
-3.500 -0.1001 0.00806 0.00215 -0.0591 0.8242 0.0025
-3.250 -0.0728 0.00783 0.00187 -0.0589 0.8154 0.0039
-2.750 -0.0181 0.00749 0.00149 -0.0586 0.7954 0.0151
-2.500 0.0091 0.00727 0.00133 -0.0585 0.7844 0.0363
-2.250 0.0358 0.00695 0.00117 -0.0584 0.7722 0.0894
-2.000 0.0625 0.00668 0.00105 -0.0582 0.7584 0.1470
-1.750 0.0894 0.00649 0.00096 -0.0581 0.7427 0.1953
-1.500 0.1160 0.00633 0.00087 -0.0579 0.7238 0.2476
-1.250 0.1428 0.00622 0.00081 -0.0578 0.7023 0.2951
-1.000 0.1695 0.00612 0.00076 -0.0576 0.6812 0.3443
-0.750 0.1962 0.00601 0.00074 -0.0574 0.6600 0.4015
-0.500 0.2228 0.00593 0.00072 -0.0572 0.6394 0.4541
-0.250 0.2495 0.00586 0.00072 -0.0571 0.6184 0.5069
0.000 0.2761 0.00580 0.00073 -0.0569 0.5991 0.5611
0.250 0.3026 0.00574 0.00075 -0.0567 0.5792 0.6164
0.500 0.3290 0.00570 0.00079 -0.0564 0.5600 0.6685
0.750 0.3552 0.00567 0.00083 -0.0561 0.5404 0.7200
1.000 0.3810 0.00565 0.00088 -0.0556 0.5204 0.7705
1.250 0.4063 0.00563 0.00094 -0.0550 0.4995 0.8206
1.500 0.4308 0.00563 0.00102 -0.0542 0.4785 0.8709
1.750 0.4551 0.00565 0.00109 -0.0533 0.4571 0.9223
2.000 0.4900 0.00576 0.00115 -0.0548 0.4324 0.9684
2.250 0.5281 0.00593 0.00122 -0.0572 0.4074 0.9936
2.500 0.5575 0.00612 0.00131 -0.0577 0.3847 1.0000
2.750 0.5832 0.00630 0.00142 -0.0573 0.3626 1.0000
3.000 0.6090 0.00650 0.00152 -0.0570 0.3404 1.0000
3.250 0.6347 0.00672 0.00164 -0.0567 0.3167 1.0000
3.500 0.6604 0.00695 0.00177 -0.0563 0.2928 1.0000
3.750 0.6862 0.00718 0.00193 -0.0560 0.2720 1.0000
4.000 0.7119 0.00742 0.00209 -0.0557 0.2494 1.0000
4.250 0.7376 0.00767 0.00225 -0.0554 0.2286 1.0000
4.750 0.7888 0.00819 0.00264 -0.0548 0.1895 1.0000
5.000 0.8133 0.00857 0.00288 -0.0543 0.1584 1.0000
5.250 0.8382 0.00893 0.00312 -0.0539 0.1344 1.0000
5.500 0.8632 0.00925 0.00338 -0.0535 0.1162 1.0000
5.750 0.8882 0.00958 0.00364 -0.0531 0.1001 1.0000
6.000 0.9132 0.00990 0.00391 -0.0528 0.0863 1.0000
6.250 0.9379 0.01025 0.00423 -0.0523 0.0722 1.0000
6.500 0.9622 0.01065 0.00456 -0.0519 0.0568 1.0000
6.750 0.9855 0.01115 0.00496 -0.0513 0.0389 1.0000
7.000 1.0078 0.01176 0.00544 -0.0505 0.0205 1.0000
7.250 1.0310 0.01225 0.00589 -0.0499 0.0121 1.0000
7.500 1.0549 0.01266 0.00629 -0.0494 0.0082 1.0000
7.750 1.0772 0.01322 0.00683 -0.0487 0.0034 1.0000
8.000 1.1005 0.01366 0.00729 -0.0481 0.0023 1.0000
8.250 1.1233 0.01417 0.00786 -0.0473 0.0015 1.0000
8.500 1.1462 0.01461 0.00836 -0.0467 0.0012 1.0000
8.750 1.1686 0.01511 0.00892 -0.0460 0.0010 1.0000
9.000 1.1905 0.01564 0.00950 -0.0452 0.0009 1.0000
9.250 1.2115 0.01624 0.01016 -0.0443 0.0007 1.0000
9.500 1.2313 0.01695 0.01097 -0.0432 0.0006 1.0000
9.750 1.2508 0.01765 0.01176 -0.0420 0.0005 1.0000
10.000 1.2706 0.01827 0.01244 -0.0410 0.0005 1.0000
10.250 1.2897 0.01890 0.01315 -0.0399 0.0005 1.0000
10.500 1.3076 0.01962 0.01398 -0.0386 0.0004 1.0000
10.750 1.3241 0.02042 0.01488 -0.0371 0.0004 1.0000
11.000 1.3392 0.02127 0.01583 -0.0355 0.0004 1.0000
11.250 1.3524 0.02218 0.01683 -0.0336 0.0003 1.0000
11.500 1.3609 0.02314 0.01792 -0.0309 0.0003 1.0000
11.750 1.3678 0.02416 0.01904 -0.0281 0.0003 1.0000
12.000 1.3728 0.02533 0.02034 -0.0253 0.0003 1.0000
12.250 1.3775 0.02658 0.02171 -0.0227 0.0003 1.0000
12.500 1.3800 0.02805 0.02331 -0.0201 0.0002 1.0000
12.750 1.3829 0.02957 0.02496 -0.0180 0.0003 1.0000
13.000 1.3819 0.03148 0.02701 -0.0158 0.0002 1.0000
13.250 1.3796 0.03366 0.02933 -0.0139 0.0002 1.0000
13.500 1.3748 0.03622 0.03206 -0.0124 0.0002 1.0000
13.750 1.3734 0.03865 0.03461 -0.0115 0.0002 1.0000
14.000 1.3649 0.04203 0.03817 -0.0110 0.0002 1.0000
14.250 1.3590 0.04544 0.04173 -0.0111 0.0002 1.0000
14.500 1.3496 0.04958 0.04602 -0.0119 0.0002 1.0000
14.750 1.3374 0.05450 0.05111 -0.0135 0.0002 1.0000
15.000 1.3218 0.06038 0.05715 -0.0159 0.0002 1.0000
15.250 1.3080 0.06644 0.06336 -0.0188 0.0002 1.0000
15.500 1.2868 0.07428 0.07138 -0.0230 0.0002 1.0000
15.750 1.2677 0.08223 0.07948 -0.0273 0.0002 1.0000
16.000 1.2453 0.09124 0.08865 -0.0324 0.0002 1.0000
16.250 1.2253 0.10015 0.09768 -0.0374 0.0002 1.0000
16.500 1.2025 0.10997 0.10761 -0.0428 0.0002 1.0000
16.750 1.1714 0.12205 0.11984 -0.0496 0.0002 1.0000
17.000 1.1514 0.13182 0.12972 -0.0550 0.0002 1.0000
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Polar data table (+)
Polar graphs
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