WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Reynolds number: 100,000 Max Cl/Cd: 39.67 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72150b-il-100000-n5.txt Download as CSV file: xf-fx72150b-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.2641 0.10551 0.09926 -0.1490 0.7614 0.0401
-10.000 0.2719 0.10338 0.09709 -0.1498 0.7568 0.0412
-9.750 0.2769 0.10170 0.09542 -0.1509 0.7520 0.0425
-9.500 0.2766 0.10082 0.09457 -0.1522 0.7466 0.0432
-9.250 0.2888 0.09756 0.09127 -0.1524 0.7428 0.0440
-9.000 0.3005 0.09502 0.08869 -0.1526 0.7390 0.0451
-8.750 0.3083 0.09311 0.08679 -0.1529 0.7339 0.0468
-8.500 0.3148 0.09123 0.08489 -0.1535 0.7296 0.0485
-8.250 0.3184 0.08975 0.08338 -0.1548 0.7262 0.0499
-8.000 0.3176 0.08883 0.08250 -0.1560 0.7216 0.0504
-7.750 0.3148 0.08789 0.08161 -0.1569 0.7166 0.0506
-7.500 0.3326 0.08405 0.07774 -0.1561 0.7134 0.0514
-7.250 0.3460 0.08154 0.07517 -0.1561 0.7104 0.0525
-7.000 0.3537 0.07967 0.07329 -0.1560 0.7068 0.0538
-6.750 0.3572 0.07818 0.07186 -0.1556 0.7020 0.0551
-6.500 0.3603 0.07663 0.07033 -0.1555 0.6981 0.0566
-6.250 0.3575 0.07554 0.06924 -0.1557 0.6947 0.0583
-6.000 0.3531 0.07478 0.06852 -0.1581 0.6909 0.0592
-5.750 0.3538 0.07346 0.06727 -0.1611 0.6858 0.0595
-5.500 0.3631 0.07066 0.06448 -0.1579 0.6827 0.0602
-5.250 0.3754 0.06843 0.06220 -0.1566 0.6798 0.0615
-5.000 0.3888 0.06629 0.06001 -0.1578 0.6774 0.0627
-4.750 0.3920 0.06494 0.05872 -0.1576 0.6731 0.0640
-4.500 0.3982 0.06331 0.05712 -0.1586 0.6690 0.0657
-4.250 0.4375 0.05827 0.05195 -0.1785 0.6654 0.0703
-4.000 0.4372 0.05754 0.05128 -0.1698 0.6633 0.0722
-3.750 0.4576 0.05554 0.04921 -0.1711 0.6613 0.0759
-3.250 0.5761 0.03953 0.03222 -0.2063 0.6547 0.0369
-3.000 0.6133 0.03704 0.02946 -0.2114 0.6517 0.0362
-2.750 0.6606 0.03419 0.02613 -0.2179 0.6495 0.0356
-2.500 0.7078 0.03179 0.02316 -0.2235 0.6475 0.0354
-2.250 0.7538 0.02991 0.02057 -0.2279 0.6459 0.0372
-2.000 0.7894 0.02900 0.01950 -0.2301 0.6444 0.0393
-1.750 0.8118 0.02869 0.01903 -0.2301 0.6409 0.0403
-1.500 0.8344 0.02844 0.01862 -0.2298 0.6373 0.0413
-1.250 0.8617 0.02803 0.01801 -0.2302 0.6346 0.0429
-1.000 0.8907 0.02770 0.01766 -0.2309 0.6324 0.0465
-0.750 0.9213 0.02737 0.01722 -0.2316 0.6307 0.0511
-0.500 0.9538 0.02704 0.01685 -0.2328 0.6292 0.0569
-0.250 0.9890 0.02676 0.01647 -0.2345 0.6280 0.0670
0.000 0.9961 0.02785 0.01768 -0.2322 0.6237 0.0759
0.250 1.0154 0.02839 0.01830 -0.2318 0.6205 0.1023
0.500 1.0496 0.02806 0.01892 -0.2343 0.6182 0.4632
0.750 1.0718 0.02853 0.01947 -0.2333 0.6161 0.5636
1.000 1.0949 0.02887 0.01982 -0.2321 0.6145 0.6263
1.250 1.1209 0.02901 0.01991 -0.2316 0.6131 0.6629
1.500 1.1529 0.02906 0.01979 -0.2324 0.6120 0.6761
1.750 1.0960 0.03327 0.02435 -0.2215 0.6026 0.6789
2.000 1.1130 0.03411 0.02510 -0.2205 0.6003 0.6886
2.250 1.1373 0.03451 0.02542 -0.2203 0.5988 0.6975
2.500 1.1658 0.03475 0.02554 -0.2208 0.5976 0.7074
2.750 1.1965 0.03480 0.02550 -0.2215 0.5967 0.7152
3.000 1.2298 0.03478 0.02537 -0.2225 0.5958 0.7242
5.000 1.1127 0.06545 0.05695 -0.1968 0.5475 1.0000
5.500 1.1075 0.07219 0.06372 -0.1943 0.5342 1.0000
5.750 1.1326 0.07277 0.06423 -0.1944 0.5331 1.0000
6.000 1.1582 0.07326 0.06465 -0.1944 0.5322 1.0000
6.500 1.1433 0.08135 0.07283 -0.1918 0.5185 1.0000
6.750 1.1681 0.08184 0.07329 -0.1917 0.5172 1.0000
7.000 1.1935 0.08227 0.07368 -0.1917 0.5163 1.0000
7.500 1.1845 0.08976 0.08129 -0.1895 0.5030 1.0000
7.750 1.2104 0.08997 0.08149 -0.1894 0.5017 1.0000
8.250 1.2159 0.09546 0.08707 -0.1877 0.4886 1.0000
8.500 1.2399 0.09581 0.08743 -0.1875 0.4871 1.0000
8.750 1.2649 0.09608 0.08770 -0.1873 0.4860 1.0000
9.250 1.2661 0.10229 0.09407 -0.1858 0.4723 1.0000
9.500 1.2908 0.10245 0.09426 -0.1856 0.4710 1.0000
10.000 1.2937 0.10859 0.10055 -0.1844 0.4575 1.0000
10.250 1.3180 0.10867 0.10070 -0.1841 0.4559 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il)