WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Reynolds number: 1,000,000 Max Cl/Cd: 154 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72150a-il-1000000-n5.txt Download as CSV file: xf-fx72150a-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2019 0.08802 0.08433 -0.1418 0.6257 0.0107
-9.500 0.2087 0.08541 0.08171 -0.1430 0.6223 0.0108
-9.250 0.2152 0.08277 0.07907 -0.1441 0.6190 0.0108
-9.000 0.2223 0.08029 0.07659 -0.1451 0.6154 0.0108
-8.750 0.2285 0.07768 0.07396 -0.1461 0.6121 0.0108
-8.500 0.2357 0.07517 0.07146 -0.1472 0.6095 0.0108
-8.000 0.2443 0.06932 0.06563 -0.1492 0.6036 0.0109
-7.500 0.2571 0.06489 0.06120 -0.1507 0.5973 0.0110
-7.250 0.2623 0.06253 0.05885 -0.1514 0.5947 0.0111
-5.750 0.2998 0.04544 0.04182 -0.1641 0.5784 0.0106
-5.500 0.3235 0.03835 0.03471 -0.1775 0.5762 0.0105
-5.250 0.3557 0.02999 0.02605 -0.1913 0.5739 0.0104
-5.000 0.4080 0.01502 0.00964 -0.2081 0.5719 0.0090
-4.750 0.4396 0.01364 0.00797 -0.2098 0.5691 0.0089
-4.500 0.4700 0.01283 0.00697 -0.2108 0.5664 0.0090
-4.000 0.5299 0.01176 0.00564 -0.2124 0.5617 0.0091
-3.750 0.5599 0.01135 0.00515 -0.2132 0.5598 0.0092
-3.500 0.5898 0.01100 0.00473 -0.2139 0.5577 0.0094
-3.250 0.6196 0.01072 0.00437 -0.2145 0.5556 0.0096
-3.000 0.6492 0.01047 0.00407 -0.2151 0.5534 0.0099
-2.750 0.6787 0.01028 0.00382 -0.2156 0.5510 0.0102
-2.500 0.7079 0.01013 0.00361 -0.2161 0.5486 0.0104
-2.250 0.7371 0.01002 0.00345 -0.2166 0.5464 0.0107
-2.000 0.7667 0.00990 0.00331 -0.2172 0.5449 0.0108
-1.750 0.7966 0.00972 0.00310 -0.2178 0.5432 0.0112
-1.500 0.8261 0.00961 0.00297 -0.2183 0.5414 0.0115
-1.250 0.8553 0.00955 0.00288 -0.2188 0.5395 0.0119
-1.000 0.8843 0.00950 0.00282 -0.2192 0.5378 0.0124
-0.750 0.9131 0.00948 0.00278 -0.2196 0.5361 0.0131
-0.500 0.9418 0.00947 0.00274 -0.2199 0.5344 0.0139
-0.250 0.9703 0.00947 0.00273 -0.2203 0.5327 0.0151
0.000 0.9986 0.00948 0.00275 -0.2206 0.5308 0.0218
0.250 1.0273 0.00948 0.00276 -0.2209 0.5295 0.0310
0.500 1.0568 0.00939 0.00278 -0.2215 0.5284 0.0741
0.750 1.0865 0.00924 0.00282 -0.2223 0.5272 0.1598
1.000 1.1178 0.00883 0.00290 -0.2237 0.5258 0.3917
1.250 1.1463 0.00881 0.00303 -0.2241 0.5243 0.4764
1.500 1.1742 0.00886 0.00312 -0.2243 0.5228 0.4957
1.750 1.2020 0.00894 0.00321 -0.2245 0.5212 0.5098
2.000 1.2295 0.00902 0.00329 -0.2246 0.5196 0.5180
2.250 1.2569 0.00911 0.00337 -0.2247 0.5182 0.5240
2.500 1.2841 0.00920 0.00347 -0.2248 0.5168 0.5302
2.750 1.3110 0.00931 0.00358 -0.2249 0.5152 0.5345
3.000 1.3379 0.00942 0.00368 -0.2250 0.5136 0.5383
3.250 1.3654 0.00950 0.00377 -0.2251 0.5125 0.5419
3.500 1.3928 0.00957 0.00388 -0.2253 0.5113 0.5460
3.750 1.4200 0.00965 0.00398 -0.2254 0.5100 0.5499
4.000 1.4469 0.00974 0.00410 -0.2255 0.5087 0.5540
4.250 1.4736 0.00983 0.00423 -0.2256 0.5075 0.5582
4.500 1.5002 0.00993 0.00435 -0.2256 0.5063 0.5628
4.750 1.5263 0.01004 0.00449 -0.2256 0.5045 0.5681
5.000 1.5506 0.01020 0.00463 -0.2252 0.5000 0.5733
5.500 1.6014 0.01043 0.00492 -0.2249 0.4928 0.5834
5.750 1.6262 0.01056 0.00508 -0.2247 0.4898 0.5893
6.000 1.6494 0.01074 0.00527 -0.2241 0.4859 0.5949
6.250 1.6720 0.01092 0.00548 -0.2235 0.4817 0.6010
6.500 1.6965 0.01104 0.00565 -0.2232 0.4784 0.6079
6.750 1.7190 0.01121 0.00586 -0.2225 0.4738 0.6151
7.000 1.7361 0.01147 0.00613 -0.2208 0.4680 0.6234
7.500 1.7689 0.01203 0.00671 -0.2172 0.4443 0.6412
7.750 1.7671 0.01295 0.00747 -0.2124 0.4135 0.6495
8.000 1.7524 0.01459 0.00890 -0.2058 0.3698 0.6584
8.250 1.7338 0.01672 0.01083 -0.1994 0.3333 0.6672
8.500 1.7114 0.01943 0.01335 -0.1930 0.2905 0.6772
8.750 1.7009 0.02174 0.01556 -0.1888 0.2637 0.6904
9.000 1.6780 0.02512 0.01879 -0.1835 0.2260 0.7059
9.250 1.6570 0.02868 0.02224 -0.1790 0.1925 0.7257
9.500 1.6349 0.03266 0.02613 -0.1750 0.1583 0.7591
9.750 1.6057 0.03724 0.03083 -0.1706 0.1192 1.0000
10.000 1.5776 0.04258 0.03599 -0.1672 0.0787 1.0000
10.250 1.5568 0.04752 0.04078 -0.1645 0.0445 1.0000
10.500 1.5391 0.05235 0.04549 -0.1624 0.0129 1.0000
10.750 1.5438 0.05479 0.04795 -0.1614 0.0098 1.0000
11.000 1.5504 0.05707 0.05026 -0.1607 0.0088 1.0000
11.250 1.5581 0.05923 0.05246 -0.1600 0.0083 1.0000
11.500 1.5648 0.06154 0.05481 -0.1594 0.0079 1.0000
11.750 1.5725 0.06374 0.05705 -0.1587 0.0076 1.0000
12.000 1.5786 0.06618 0.05953 -0.1582 0.0073 1.0000
12.250 1.5853 0.06855 0.06195 -0.1576 0.0071 1.0000
12.500 1.5920 0.07096 0.06440 -0.1571 0.0069 1.0000
12.750 1.5985 0.07342 0.06691 -0.1566 0.0068 1.0000
13.000 1.6058 0.07576 0.06930 -0.1562 0.0067 1.0000
13.250 1.6119 0.07831 0.07189 -0.1558 0.0066 1.0000
13.500 1.6182 0.08083 0.07446 -0.1555 0.0065 1.0000
13.750 1.6251 0.08328 0.07696 -0.1551 0.0064 1.0000
14.000 1.6305 0.08599 0.07973 -0.1549 0.0063 1.0000
14.250 1.6364 0.08861 0.08240 -0.1546 0.0062 1.0000
14.500 1.6426 0.09117 0.08501 -0.1544 0.0061 1.0000
14.750 1.6475 0.09398 0.08787 -0.1542 0.0060 1.0000
15.000 1.6526 0.09674 0.09069 -0.1541 0.0060 1.0000
15.250 1.6582 0.09942 0.09342 -0.1540 0.0059 1.0000
15.500 1.6626 0.10234 0.09640 -0.1539 0.0058 1.0000
15.750 1.6668 0.10526 0.09937 -0.1539 0.0057 1.0000
16.000 1.6715 0.10808 0.10225 -0.1540 0.0057 1.0000
16.250 1.6747 0.11117 0.10540 -0.1541 0.0056 1.0000
16.500 1.6782 0.11421 0.10850 -0.1542 0.0055 1.0000
16.750 1.6818 0.11721 0.11156 -0.1544 0.0055 1.0000
17.000 1.6836 0.12054 0.11495 -0.1547 0.0054 1.0000
17.250 1.6861 0.12373 0.11821 -0.1550 0.0054 1.0000
17.500 1.6884 0.12692 0.12146 -0.1554 0.0053 1.0000
17.750 1.6878 0.13060 0.12522 -0.1559 0.0053 1.0000
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