WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Reynolds number: 100,000 Max Cl/Cd: 40.49 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72150a-il-100000-n5.txt Download as CSV file: xf-fx72150a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 72-MS-150A 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
------ -------- --------- --------- -------- -------- --------
-11.000 0.1425 0.11242 0.10634 -0.1300 0.7980 0.0437
-10.750 0.1423 0.11107 0.10499 -0.1320 0.7918 0.0450
-10.500 0.1457 0.10914 0.10308 -0.1334 0.7856 0.0453
-10.250 0.1638 0.10539 0.09926 -0.1331 0.7808 0.0463
-10.000 0.1736 0.10307 0.09692 -0.1336 0.7751 0.0482
-9.750 0.1804 0.10093 0.09479 -0.1345 0.7689 0.0495
-9.500 0.1841 0.09912 0.09295 -0.1359 0.7640 0.0511
-9.250 0.1824 0.09778 0.09164 -0.1378 0.7583 0.0517
-8.750 0.2042 0.09210 0.08592 -0.1382 0.7484 0.0530
-8.500 0.2144 0.08982 0.08361 -0.1384 0.7436 0.0542
-8.250 0.2218 0.08774 0.08154 -0.1389 0.7383 0.0555
-8.000 0.2279 0.08568 0.07946 -0.1397 0.7339 0.0572
-7.750 0.2297 0.08389 0.07764 -0.1414 0.7302 0.0589
-7.500 0.2221 0.08262 0.07647 -0.1433 0.7242 0.0596
-7.250 0.2297 0.07998 0.07384 -0.1434 0.7198 0.0601
-7.000 0.2466 0.07725 0.07105 -0.1426 0.7164 0.0612
-6.750 0.2569 0.07511 0.06886 -0.1427 0.7134 0.0626
-6.500 0.2599 0.07344 0.06726 -0.1424 0.7082 0.0641
-6.250 0.2606 0.07187 0.06573 -0.1423 0.7036 0.0656
-6.000 0.2571 0.07001 0.06388 -0.1474 0.6995 0.0684
-5.750 0.2663 0.06669 0.06053 -0.1532 0.6966 0.0692
-5.500 0.2742 0.06481 0.05871 -0.1504 0.6921 0.0699
-5.250 0.2844 0.06278 0.05669 -0.1503 0.6880 0.0707
-5.000 0.2976 0.06039 0.05428 -0.1521 0.6845 0.0717
-4.500 0.3526 0.04550 0.03884 -0.1753 0.6785 0.0339
-4.250 0.3758 0.04249 0.03568 -0.1795 0.6740 0.0327
-4.000 0.4199 0.03662 0.02902 -0.1893 0.6706 0.0300
-3.750 0.4547 0.03404 0.02604 -0.1933 0.6678 0.0304
-3.500 0.4867 0.03252 0.02429 -0.1958 0.6654 0.0317
-3.250 0.5243 0.03051 0.02178 -0.1990 0.6634 0.0328
-3.000 0.5537 0.02912 0.02005 -0.2005 0.6600 0.0328
-2.750 0.5823 0.02801 0.01863 -0.2014 0.6565 0.0328
-2.500 0.6116 0.02705 0.01738 -0.2022 0.6535 0.0331
-2.250 0.6415 0.02619 0.01628 -0.2028 0.6510 0.0336
-2.000 0.6718 0.02545 0.01533 -0.2034 0.6489 0.0344
-1.750 0.7022 0.02483 0.01465 -0.2041 0.6471 0.0356
-1.500 0.7304 0.02449 0.01427 -0.2045 0.6449 0.0375
-1.250 0.7515 0.02461 0.01443 -0.2039 0.6411 0.0408
-1.000 0.7768 0.02460 0.01438 -0.2040 0.6379 0.0458
-0.750 0.8055 0.02444 0.01415 -0.2045 0.6352 0.0524
-0.500 0.8370 0.02418 0.01390 -0.2058 0.6331 0.0741
-0.250 0.8748 0.02322 0.01415 -0.2089 0.6315 0.4772
0.000 0.9002 0.02363 0.01461 -0.2079 0.6299 0.5782
0.250 0.9163 0.02432 0.01539 -0.2056 0.6273 0.6298
0.500 0.9309 0.02507 0.01616 -0.2037 0.6235 0.6487
0.750 0.9519 0.02552 0.01654 -0.2030 0.6206 0.6579
1.000 0.9776 0.02583 0.01673 -0.2030 0.6182 0.6663
1.250 1.0044 0.02603 0.01683 -0.2031 0.6163 0.6735
1.500 1.0338 0.02619 0.01685 -0.2036 0.6146 0.6822
1.750 1.0638 0.02627 0.01681 -0.2041 0.6132 0.6891
2.000 1.0748 0.02733 0.01792 -0.2023 0.6096 0.6954
2.250 1.0811 0.02865 0.01930 -0.1998 0.6056 0.7012
2.500 1.0969 0.02948 0.02013 -0.1986 0.6028 0.7079
2.750 1.1188 0.03005 0.02066 -0.1982 0.6008 0.7162
3.000 1.1434 0.03042 0.02100 -0.1980 0.5991 0.7244
3.250 1.1715 0.03065 0.02119 -0.1984 0.5978 0.7336
3.500 1.2015 0.03075 0.02127 -0.1990 0.5966 0.7435
4.500 1.1883 0.03814 0.02913 -0.1851 0.5803 0.8085
4.750 1.2120 0.03807 0.02917 -0.1844 0.5794 1.0000
6.750 1.1119 0.07021 0.06170 -0.1665 0.5203 1.0000
7.000 1.1320 0.07114 0.06263 -0.1662 0.5179 1.0000
7.250 1.1555 0.07171 0.06322 -0.1660 0.5162 1.0000
7.500 1.1826 0.07183 0.06334 -0.1660 0.5150 1.0000
7.750 1.2105 0.07178 0.06330 -0.1658 0.5138 1.0000
8.250 1.2115 0.07737 0.06901 -0.1636 0.4996 1.0000
8.500 1.2386 0.07737 0.06906 -0.1635 0.4985 1.0000
9.000 1.2384 0.08341 0.07524 -0.1616 0.4844 1.0000
9.250 1.2649 0.08338 0.07526 -0.1613 0.4831 1.0000
9.750 1.2690 0.08886 0.08092 -0.1597 0.4687 1.0000
10.000 1.2895 0.08938 0.08151 -0.1593 0.4659 1.0000
10.500 1.3050 0.09335 0.08566 -0.1580 0.4527 1.0000
11.000 1.3179 0.09777 0.09029 -0.1568 0.4389 1.0000
11.250 1.3439 0.09743 0.09004 -0.1564 0.4372 1.0000
11.750 1.3588 0.10153 0.09437 -0.1554 0.4235 1.0000
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Polar data table (+)
Polar graphs
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