MH 150 23.89% (mh150-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 150 23.89% (mh150-il) Reynolds number: 200,000 Max Cl/Cd: 61.44 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh150-il-200000-n5.txt Download as CSV file: xf-mh150-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 150 23.89%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.5260 0.09589 0.09074 -0.0790 0.9328 0.0406
-16.250 -0.5286 0.09230 0.08709 -0.0804 0.9188 0.0421
-15.750 -0.5354 0.08511 0.07975 -0.0832 0.8938 0.0457
-15.500 -0.5404 0.08142 0.07599 -0.0845 0.8832 0.0474
-15.250 -0.5435 0.07783 0.07233 -0.0861 0.8726 0.0495
-14.750 -0.5494 0.07079 0.06514 -0.0893 0.8538 0.0542
-14.500 -0.5510 0.06748 0.06173 -0.0908 0.8447 0.0570
-14.250 -0.5542 0.06393 0.05812 -0.0927 0.8366 0.0597
-14.000 -0.5544 0.06075 0.05486 -0.0944 0.8278 0.0630
-13.750 -0.5572 0.05737 0.05140 -0.0962 0.8201 0.0663
-13.500 -0.5571 0.05422 0.04818 -0.0981 0.8122 0.0700
-13.250 -0.5573 0.05114 0.04503 -0.0999 0.8041 0.0741
-13.000 -0.5576 0.04814 0.04195 -0.1016 0.7969 0.0782
-12.500 -0.5542 0.04249 0.03619 -0.1054 0.7816 0.0877
-12.250 -0.5517 0.03995 0.03355 -0.1069 0.7749 0.0928
-12.000 -0.5471 0.03752 0.03109 -0.1087 0.7675 0.0986
-11.750 -0.5431 0.03511 0.02863 -0.1104 0.7600 0.1044
-11.500 -0.5364 0.03300 0.02644 -0.1119 0.7535 0.1107
-11.250 -0.5276 0.03102 0.02442 -0.1135 0.7466 0.1178
-11.000 -0.5188 0.02907 0.02244 -0.1152 0.7393 0.1248
-10.750 -0.5076 0.02741 0.02071 -0.1166 0.7328 0.1322
-10.500 -0.4970 0.02602 0.01927 -0.1175 0.7266 0.1401
-10.250 -0.4837 0.02460 0.01784 -0.1192 0.7195 0.1482
-10.000 -0.4654 0.02338 0.01656 -0.1210 0.7130 0.1570
-9.750 -0.4435 0.02233 0.01543 -0.1230 0.7073 0.1668
-9.500 -0.4191 0.02129 0.01440 -0.1256 0.7005 0.1776
-9.250 -0.3917 0.02042 0.01351 -0.1282 0.6941 0.1889
-9.000 -0.3622 0.01974 0.01275 -0.1306 0.6884 0.2002
-8.750 -0.3319 0.01922 0.01215 -0.1326 0.6822 0.2111
-8.500 -0.3014 0.01878 0.01170 -0.1344 0.6757 0.2210
-8.250 -0.2708 0.01843 0.01127 -0.1359 0.6700 0.2299
-8.000 -0.2397 0.01816 0.01087 -0.1373 0.6648 0.2389
-7.750 -0.2089 0.01789 0.01058 -0.1386 0.6583 0.2466
-7.500 -0.1777 0.01768 0.01029 -0.1398 0.6520 0.2546
-7.250 -0.1464 0.01748 0.00995 -0.1409 0.6466 0.2619
-7.000 -0.1154 0.01732 0.00977 -0.1420 0.6414 0.2685
-6.750 -0.0838 0.01716 0.00951 -0.1431 0.6353 0.2756
-6.500 -0.0529 0.01701 0.00929 -0.1440 0.6293 0.2813
-6.250 -0.0219 0.01690 0.00910 -0.1449 0.6241 0.2872
-6.000 0.0096 0.01678 0.00890 -0.1459 0.6184 0.2934
-5.750 0.0408 0.01666 0.00871 -0.1468 0.6127 0.2988
-5.500 0.0715 0.01656 0.00859 -0.1476 0.6072 0.3038
-5.000 0.1342 0.01641 0.00825 -0.1494 0.5964 0.3148
-4.750 0.1649 0.01633 0.00814 -0.1501 0.5907 0.3196
-4.500 0.1956 0.01627 0.00805 -0.1508 0.5856 0.3245
-4.250 0.2268 0.01624 0.00791 -0.1516 0.5809 0.3299
-4.000 0.2582 0.01620 0.00781 -0.1525 0.5752 0.3352
-3.750 0.2886 0.01614 0.00775 -0.1532 0.5696 0.3399
-3.500 0.3192 0.01612 0.00769 -0.1539 0.5646 0.3450
-3.250 0.3503 0.01613 0.00761 -0.1546 0.5602 0.3505
-3.000 0.3815 0.01612 0.00755 -0.1555 0.5549 0.3559
-2.750 0.4118 0.01610 0.00754 -0.1561 0.5495 0.3605
-2.500 0.4421 0.01610 0.00751 -0.1567 0.5446 0.3652
-2.250 0.4728 0.01614 0.00747 -0.1574 0.5403 0.3706
-2.000 0.5037 0.01617 0.00747 -0.1582 0.5355 0.3764
-1.750 0.5339 0.01619 0.00750 -0.1588 0.5306 0.3813
-1.500 0.5640 0.01623 0.00753 -0.1594 0.5259 0.3863
-1.250 0.5944 0.01630 0.00752 -0.1601 0.5216 0.3921
-1.000 0.6248 0.01637 0.00756 -0.1608 0.5169 0.3985
-0.750 0.6546 0.01643 0.00767 -0.1613 0.5122 0.4042
-0.500 0.6845 0.01651 0.00775 -0.1619 0.5079 0.4105
-0.250 0.7145 0.01662 0.00778 -0.1625 0.5039 0.4170
0.000 0.7445 0.01673 0.00785 -0.1631 0.5001 0.4232
0.250 0.7738 0.01683 0.00803 -0.1636 0.4956 0.4299
0.500 0.8031 0.01695 0.00815 -0.1641 0.4910 0.4377
0.750 0.8324 0.01709 0.00825 -0.1646 0.4867 0.4449
1.000 0.8613 0.01724 0.00839 -0.1650 0.4831 0.4519
1.250 0.8905 0.01740 0.00855 -0.1655 0.4796 0.4596
1.500 0.9193 0.01756 0.00874 -0.1660 0.4756 0.4670
1.750 0.9474 0.01773 0.00896 -0.1663 0.4716 0.4746
2.000 0.9757 0.01792 0.00913 -0.1666 0.4677 0.4835
2.250 1.0037 0.01811 0.00929 -0.1669 0.4640 0.4914
2.500 1.0314 0.01833 0.00953 -0.1671 0.4605 0.4993
2.750 1.0588 0.01855 0.00978 -0.1674 0.4567 0.5078
3.000 1.0856 0.01877 0.01006 -0.1675 0.4530 0.5151
3.250 1.1122 0.01901 0.01032 -0.1676 0.4495 0.5235
3.500 1.1394 0.01926 0.01053 -0.1678 0.4463 0.5328
3.750 1.1658 0.01953 0.01080 -0.1678 0.4432 0.5404
4.000 1.1908 0.01981 0.01116 -0.1676 0.4397 0.5487
4.250 1.2158 0.02010 0.01148 -0.1676 0.4359 0.5572
4.500 1.2395 0.02040 0.01185 -0.1672 0.4324 0.5645
4.750 1.2640 0.02071 0.01217 -0.1669 0.4293 0.5733
5.000 1.2889 0.02103 0.01247 -0.1668 0.4264 0.5817
5.250 1.3130 0.02137 0.01282 -0.1665 0.4237 0.5891
5.500 1.3333 0.02175 0.01329 -0.1657 0.4206 0.5976
5.750 1.3529 0.02214 0.01375 -0.1648 0.4171 0.6054
6.000 1.3724 0.02256 0.01425 -0.1639 0.4138 0.6125
6.250 1.3935 0.02300 0.01470 -0.1633 0.4106 0.6210
6.500 1.4157 0.02343 0.01512 -0.1629 0.4079 0.6289
6.750 1.4383 0.02385 0.01553 -0.1624 0.4055 0.6359
7.000 1.4555 0.02445 0.01625 -0.1614 0.4026 0.6440
7.250 1.4729 0.02508 0.01696 -0.1605 0.3993 0.6516
7.500 1.4889 0.02571 0.01770 -0.1594 0.3961 0.6580
7.750 1.5064 0.02634 0.01836 -0.1585 0.3931 0.6657
8.000 1.5260 0.02693 0.01894 -0.1580 0.3904 0.6737
8.250 1.5456 0.02746 0.01949 -0.1572 0.3880 0.6797
8.500 1.5609 0.02825 0.02036 -0.1562 0.3853 0.6868
8.750 1.5737 0.02922 0.02144 -0.1551 0.3821 0.6945
9.000 1.5858 0.03017 0.02250 -0.1538 0.3789 0.7002
9.250 1.5991 0.03110 0.02350 -0.1527 0.3760 0.7066
9.500 1.6152 0.03192 0.02434 -0.1520 0.3734 0.7142
9.750 1.6329 0.03263 0.02504 -0.1513 0.3708 0.7205
10.000 1.6474 0.03351 0.02599 -0.1503 0.3682 0.7264
10.250 1.6537 0.03502 0.02763 -0.1490 0.3650 0.7330
10.500 1.6622 0.03645 0.02917 -0.1480 0.3619 0.7398
10.750 1.6699 0.03783 0.03065 -0.1467 0.3588 0.7450
11.000 1.6818 0.03897 0.03184 -0.1457 0.3560 0.7512
11.250 1.6980 0.03985 0.03271 -0.1452 0.3534 0.7584
11.500 1.7113 0.04087 0.03376 -0.1443 0.3508 0.7638
11.750 1.7085 0.04325 0.03633 -0.1427 0.3474 0.7691
12.000 1.7093 0.04546 0.03867 -0.1416 0.3439 0.7752
12.250 1.7135 0.04741 0.04070 -0.1407 0.3405 0.7810
12.500 1.7239 0.04871 0.04204 -0.1398 0.3377 0.7863
12.750 1.7411 0.04945 0.04276 -0.1392 0.3351 0.7929
13.250 1.7276 0.05580 0.04943 -0.1371 0.3275 0.8028
13.500 1.7247 0.05866 0.05240 -0.1363 0.3237 0.8079
13.750 1.7345 0.06025 0.05401 -0.1358 0.3206 0.8144
14.000 1.7524 0.06089 0.05462 -0.1354 0.3181 0.8203
14.250 1.7368 0.06530 0.05923 -0.1345 0.3140 0.8246
14.500 1.7166 0.07046 0.06457 -0.1339 0.3091 0.8290
14.750 1.7156 0.07347 0.06765 -0.1337 0.3053 0.8347
15.000 1.7307 0.07433 0.06851 -0.1332 0.3026 0.8404
15.250 1.7359 0.07650 0.07072 -0.1328 0.2994 0.8464
15.500 1.6849 0.08591 0.08042 -0.1328 0.2923 0.8487
15.750 1.6839 0.08899 0.08355 -0.1327 0.2884 0.8536
16.000 1.7043 0.08920 0.08375 -0.1324 0.2860 0.8605
16.250 1.6605 0.09804 0.09280 -0.1329 0.2791 0.8631
16.500 1.6383 0.10421 0.09910 -0.1335 0.2732 0.8672
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Polar data table (+)
Polar graphs
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