WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Reynolds number: 1,000,000 Max Cl/Cd: 160.23 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72150a-il-1000000.txt Download as CSV file: xf-fx72150a-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.2205 0.08639 0.08298 -0.1438 0.6710 0.0124
-9.250 0.2280 0.08401 0.08058 -0.1447 0.6667 0.0127
-9.000 0.2355 0.08166 0.07821 -0.1456 0.6624 0.0128
-8.750 0.2397 0.07858 0.07515 -0.1473 0.6590 0.0133
-8.000 0.2545 0.07046 0.06701 -0.1504 0.6469 0.0137
-7.750 0.2604 0.06785 0.06442 -0.1516 0.6435 0.0136
-7.500 0.2720 0.06641 0.06298 -0.1517 0.6397 0.0138
-7.250 0.2796 0.06441 0.06098 -0.1523 0.6357 0.0139
-7.000 0.2876 0.06275 0.05931 -0.1526 0.6316 0.0144
-6.750 0.2925 0.06062 0.05718 -0.1530 0.6281 0.0146
-6.500 0.2952 0.05844 0.05503 -0.1532 0.6248 0.0150
-6.250 0.2975 0.05622 0.05282 -0.1539 0.6213 0.0154
-6.000 0.2967 0.03412 0.03090 -0.1479 0.6101 0.0164
-5.750 0.3069 0.03182 0.02861 -0.1499 0.6073 0.0165
-5.500 0.3194 0.02930 0.02609 -0.1529 0.6045 0.0167
-5.250 0.3345 0.02612 0.02289 -0.1580 0.6018 0.0169
-5.000 0.3612 0.01997 0.01662 -0.1726 0.5995 0.0171
-4.750 0.4039 0.01268 0.00871 -0.1880 0.5974 0.0192
-4.500 0.4331 0.01001 0.00587 -0.1926 0.5950 0.0196
-4.250 0.4620 0.00899 0.00477 -0.1949 0.5929 0.0198
-4.000 0.5109 0.02066 0.01607 -0.2069 0.5941 0.0202
-3.750 0.5424 0.01926 0.01450 -0.2089 0.5918 0.0210
-3.500 0.5788 0.01692 0.01170 -0.2116 0.5893 0.0230
-3.250 0.6085 0.01603 0.01075 -0.2127 0.5867 0.0235
-3.000 0.6461 0.01266 0.00674 -0.2146 0.5841 0.0169
-2.750 0.6768 0.01156 0.00548 -0.2153 0.5812 0.0150
-2.500 0.7076 0.01079 0.00457 -0.2161 0.5785 0.0144
-2.250 0.7381 0.01039 0.00413 -0.2169 0.5766 0.0146
-2.000 0.7683 0.01011 0.00382 -0.2176 0.5743 0.0151
-1.750 0.7982 0.00991 0.00358 -0.2182 0.5720 0.0158
-1.500 0.8278 0.00977 0.00340 -0.2187 0.5697 0.0162
-1.250 0.8577 0.00959 0.00317 -0.2194 0.5675 0.0168
-1.000 0.8867 0.00954 0.00308 -0.2198 0.5651 0.0175
-0.750 0.9156 0.00954 0.00304 -0.2202 0.5627 0.0185
-0.500 0.9450 0.00947 0.00298 -0.2207 0.5613 0.0203
-0.250 0.9743 0.00942 0.00293 -0.2211 0.5597 0.0231
0.000 1.0045 0.00926 0.00287 -0.2219 0.5579 0.0663
0.250 1.0362 0.00881 0.00289 -0.2233 0.5562 0.2773
0.500 1.0661 0.00859 0.00302 -0.2242 0.5544 0.4558
0.750 1.0942 0.00865 0.00310 -0.2245 0.5526 0.4812
1.000 1.1220 0.00875 0.00320 -0.2246 0.5507 0.5062
1.250 1.1495 0.00888 0.00334 -0.2248 0.5484 0.5301
1.500 1.1773 0.00904 0.00346 -0.2249 0.5464 0.5420
1.750 1.2053 0.00909 0.00356 -0.2252 0.5454 0.5527
2.000 1.2333 0.00917 0.00364 -0.2254 0.5443 0.5591
2.250 1.2612 0.00923 0.00372 -0.2256 0.5431 0.5649
2.500 1.2890 0.00931 0.00382 -0.2258 0.5418 0.5709
2.750 1.3166 0.00940 0.00391 -0.2260 0.5403 0.5752
3.000 1.3442 0.00949 0.00400 -0.2262 0.5388 0.5789
3.250 1.3716 0.00957 0.00411 -0.2264 0.5373 0.5836
3.500 1.3988 0.00968 0.00423 -0.2265 0.5358 0.5886
3.750 1.4259 0.00981 0.00435 -0.2267 0.5343 0.5934
4.000 1.4531 0.00995 0.00449 -0.2268 0.5328 0.5982
4.250 1.4805 0.01012 0.00468 -0.2271 0.5310 0.6036
4.500 1.5078 0.01026 0.00484 -0.2273 0.5298 0.6096
4.750 1.5345 0.01032 0.00496 -0.2273 0.5286 0.6159
5.000 1.5601 0.01033 0.00503 -0.2272 0.5257 0.6229
5.250 1.5857 0.01038 0.00512 -0.2271 0.5225 0.6300
5.500 1.6116 0.01046 0.00525 -0.2270 0.5202 0.6376
5.750 1.6369 0.01059 0.00539 -0.2268 0.5179 0.6463
6.000 1.6619 0.01080 0.00561 -0.2267 0.5141 0.6551
6.500 1.7116 0.01091 0.00588 -0.2262 0.5093 0.6774
6.750 1.7361 0.01098 0.00603 -0.2259 0.5063 0.6920
7.000 1.7583 0.01110 0.00619 -0.2252 0.5016 0.7107
7.250 1.7798 0.01125 0.00640 -0.2243 0.4966 0.7360
7.500 1.8010 0.01124 0.00659 -0.2234 0.4898 0.8043
7.750 1.8104 0.01133 0.00683 -0.2201 0.4822 1.0000
8.000 1.8269 0.01156 0.00708 -0.2183 0.4719 1.0000
8.250 1.8393 0.01194 0.00744 -0.2159 0.4575 1.0000
8.500 1.8378 0.01284 0.00819 -0.2112 0.4254 1.0000
8.750 1.8245 0.01446 0.00960 -0.2050 0.3892 1.0000
9.000 1.7964 0.01718 0.01204 -0.1974 0.3415 1.0000
9.250 1.7687 0.02039 0.01502 -0.1907 0.2974 1.0000
9.500 1.7453 0.02373 0.01817 -0.1852 0.2611 1.0000
9.750 1.7197 0.02756 0.02183 -0.1801 0.2256 1.0000
10.000 1.6956 0.03164 0.02576 -0.1757 0.1927 1.0000
10.250 1.6765 0.03563 0.02964 -0.1722 0.1644 1.0000
10.500 1.6523 0.04045 0.03431 -0.1688 0.1311 1.0000
10.750 1.6300 0.04538 0.03909 -0.1659 0.0994 1.0000
11.000 1.6045 0.05094 0.04448 -0.1633 0.0633 1.0000
11.250 1.5788 0.05681 0.05017 -0.1609 0.0264 1.0000
11.500 1.5735 0.06052 0.05384 -0.1597 0.0133 1.0000
11.750 1.5793 0.06294 0.05630 -0.1590 0.0122 1.0000
12.000 1.5844 0.06548 0.05889 -0.1583 0.0114 1.0000
12.250 1.5903 0.06797 0.06142 -0.1577 0.0110 1.0000
12.500 1.5973 0.07032 0.06383 -0.1572 0.0107 1.0000
12.750 1.6028 0.07291 0.06647 -0.1567 0.0104 1.0000
13.000 1.6089 0.07541 0.06902 -0.1562 0.0102 1.0000
13.250 1.6141 0.07808 0.07174 -0.1558 0.0100 1.0000
13.500 1.6190 0.08080 0.07451 -0.1554 0.0097 1.0000
13.750 1.6242 0.08349 0.07725 -0.1550 0.0095 1.0000
14.000 1.6274 0.08651 0.08033 -0.1547 0.0094 1.0000
14.250 1.6307 0.08951 0.08339 -0.1544 0.0092 1.0000
14.500 1.6333 0.09261 0.08657 -0.1541 0.0090 1.0000
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