WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.98 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72150b-il-1000000-n5.txt Download as CSV file: xf-fx72150b-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 72-MS-150B AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 0.3129 0.08807 0.08427 -0.1598 0.6203 0.0101
-9.500 0.3205 0.08568 0.08188 -0.1608 0.6170 0.0102
-9.250 0.3267 0.08308 0.07927 -0.1620 0.6137 0.0103
-9.000 0.3350 0.08085 0.07703 -0.1629 0.6109 0.0103
-8.750 0.3426 0.07847 0.07466 -0.1638 0.6083 0.0103
-8.500 0.3506 0.07623 0.07242 -0.1647 0.6053 0.0103
-8.250 0.3592 0.07411 0.07030 -0.1654 0.6023 0.0103
-8.000 0.3701 0.07266 0.06884 -0.1658 0.5991 0.0100
-7.750 0.3769 0.07049 0.06667 -0.1664 0.5962 0.0095
-7.500 0.3832 0.06816 0.06435 -0.1671 0.5938 0.0091
-7.250 0.3900 0.06591 0.06212 -0.1678 0.5914 0.0092
-7.000 0.3959 0.06369 0.05991 -0.1684 0.5887 0.0094
-6.750 0.4007 0.06151 0.05774 -0.1688 0.5858 0.0096
-6.500 0.4039 0.05942 0.05567 -0.1688 0.5832 0.0095
-6.250 0.4034 0.05747 0.05373 -0.1683 0.5805 0.0098
-6.000 0.4097 0.05509 0.05136 -0.1697 0.5783 0.0099
-5.750 0.4187 0.05254 0.04883 -0.1719 0.5761 0.0098
-5.500 0.4898 0.01654 0.01166 -0.2346 0.5749 0.0101
-5.250 0.5274 0.01446 0.00915 -0.2385 0.5722 0.0103
-5.000 0.5615 0.01322 0.00761 -0.2409 0.5695 0.0105
-4.750 0.5930 0.01257 0.00680 -0.2423 0.5669 0.0108
-4.250 0.6537 0.01185 0.00589 -0.2442 0.5624 0.0111
-4.000 0.6841 0.01154 0.00549 -0.2451 0.5605 0.0113
-3.750 0.7144 0.01125 0.00513 -0.2460 0.5585 0.0115
-3.500 0.7446 0.01099 0.00480 -0.2468 0.5565 0.0118
-3.250 0.7746 0.01079 0.00452 -0.2475 0.5544 0.0121
-3.000 0.8042 0.01063 0.00430 -0.2481 0.5524 0.0125
-2.750 0.8336 0.01050 0.00410 -0.2487 0.5504 0.0128
-2.250 0.8935 0.01019 0.00371 -0.2502 0.5468 0.0137
-2.000 0.9231 0.01009 0.00360 -0.2508 0.5453 0.0142
-1.750 0.9525 0.01003 0.00351 -0.2514 0.5437 0.0150
-1.500 0.9817 0.00997 0.00343 -0.2519 0.5419 0.0157
-1.250 1.0109 0.00993 0.00336 -0.2524 0.5400 0.0168
-1.000 1.0397 0.00992 0.00333 -0.2529 0.5381 0.0182
-0.750 1.0683 0.00992 0.00331 -0.2533 0.5362 0.0200
-0.500 1.0964 0.00995 0.00333 -0.2536 0.5344 0.0228
-0.250 1.1245 0.00998 0.00334 -0.2539 0.5325 0.0261
0.000 1.1531 0.00998 0.00334 -0.2544 0.5312 0.0304
0.250 1.1821 0.00996 0.00337 -0.2549 0.5302 0.0467
0.500 1.2111 0.00992 0.00341 -0.2555 0.5290 0.0786
0.750 1.2405 0.00985 0.00347 -0.2562 0.5277 0.1444
1.000 1.2706 0.00970 0.00355 -0.2572 0.5263 0.2664
1.250 1.3006 0.00955 0.00369 -0.2582 0.5249 0.4239
1.500 1.3280 0.00962 0.00380 -0.2584 0.5235 0.4608
1.750 1.3551 0.00970 0.00391 -0.2585 0.5221 0.4853
2.250 1.4085 0.00991 0.00415 -0.2587 0.5194 0.5146
2.500 1.4346 0.01004 0.00426 -0.2586 0.5179 0.5211
2.750 1.4603 0.01018 0.00440 -0.2586 0.5162 0.5262
3.000 1.4870 0.01027 0.00451 -0.2587 0.5151 0.5330
3.250 1.5135 0.01036 0.00462 -0.2587 0.5140 0.5382
3.500 1.5399 0.01046 0.00474 -0.2588 0.5128 0.5429
3.750 1.5660 0.01056 0.00487 -0.2588 0.5116 0.5471
4.000 1.5917 0.01067 0.00500 -0.2588 0.5105 0.5511
4.250 1.6171 0.01080 0.00514 -0.2587 0.5093 0.5549
4.500 1.6422 0.01092 0.00530 -0.2585 0.5081 0.5591
4.750 1.6668 0.01106 0.00546 -0.2583 0.5069 0.5642
5.000 1.6910 0.01120 0.00563 -0.2580 0.5057 0.5697
5.250 1.7139 0.01136 0.00581 -0.2574 0.5045 0.5747
5.500 1.7355 0.01152 0.00600 -0.2566 0.5033 0.5802
5.750 1.7562 0.01171 0.00621 -0.2556 0.5019 0.5860
6.000 1.7772 0.01191 0.00645 -0.2548 0.5005 0.5914
6.250 1.7997 0.01206 0.00666 -0.2542 0.4994 0.5976
6.500 1.8219 0.01223 0.00688 -0.2536 0.4982 0.6045
6.750 1.8437 0.01241 0.00711 -0.2529 0.4967 0.6115
7.000 1.8638 0.01262 0.00739 -0.2519 0.4940 0.6199
7.250 1.8816 0.01291 0.00771 -0.2506 0.4904 0.6288
7.500 1.8968 0.01331 0.00812 -0.2489 0.4866 0.6391
7.750 1.9162 0.01360 0.00848 -0.2479 0.4838 0.6498
8.000 1.9361 0.01387 0.00882 -0.2471 0.4810 0.6609
8.250 1.9536 0.01424 0.00925 -0.2458 0.4770 0.6737
8.500 1.9670 0.01479 0.00983 -0.2440 0.4721 0.6899
8.750 1.9834 0.01524 0.01038 -0.2427 0.4674 0.7144
9.000 1.9992 0.01572 0.01099 -0.2414 0.4596 0.7732
9.250 2.0070 0.01625 0.01174 -0.2387 0.4511 1.0000
9.500 2.0111 0.01743 0.01287 -0.2358 0.4330 1.0000
9.750 2.0046 0.01934 0.01468 -0.2317 0.4132 1.0000
10.000 1.9985 0.02139 0.01667 -0.2278 0.3938 1.0000
10.250 1.9782 0.02457 0.01970 -0.2225 0.3613 1.0000
10.500 1.9595 0.02788 0.02292 -0.2178 0.3404 1.0000
10.750 1.9433 0.03126 0.02623 -0.2137 0.3176 1.0000
11.000 1.9193 0.03565 0.03052 -0.2093 0.2921 1.0000
11.250 1.9001 0.03989 0.03468 -0.2057 0.2700 1.0000
11.500 1.8764 0.04489 0.03960 -0.2022 0.2456 1.0000
11.750 1.8513 0.05028 0.04489 -0.1989 0.2198 1.0000
12.000 1.8292 0.05562 0.05014 -0.1962 0.1959 1.0000
12.250 1.8070 0.06119 0.05562 -0.1937 0.1725 1.0000
12.500 1.7890 0.06646 0.06080 -0.1917 0.1491 1.0000
12.750 1.7734 0.07157 0.06582 -0.1901 0.1273 1.0000
13.000 1.7634 0.07607 0.07026 -0.1888 0.1099 1.0000
13.250 1.7513 0.08098 0.07510 -0.1876 0.0897 1.0000
13.500 1.7329 0.08683 0.08080 -0.1864 0.0627 1.0000
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Polar data table (+)
Polar graphs
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