WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Reynolds number: 200,000 Max Cl/Cd: 58.17 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72150a-il-200000.txt Download as CSV file: xf-fx72150a-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.1818 0.10264 0.09798 -0.1392 0.7984 0.0341
-10.250 0.1822 0.10105 0.09638 -0.1410 0.7926 0.0345
-10.000 0.1878 0.09852 0.09386 -0.1419 0.7866 0.0347
-9.750 0.2035 0.09552 0.09080 -0.1418 0.7817 0.0352
-9.500 0.2136 0.09327 0.08853 -0.1423 0.7767 0.0360
-9.250 0.2213 0.09113 0.08639 -0.1429 0.7708 0.0369
-9.000 0.2288 0.08893 0.08416 -0.1438 0.7658 0.0379
-8.750 0.2313 0.08693 0.08214 -0.1455 0.7613 0.0391
-8.500 0.2255 0.08529 0.08057 -0.1481 0.7551 0.0395
-8.250 0.2446 0.08218 0.07741 -0.1469 0.7508 0.0402
-8.000 0.2574 0.08002 0.07518 -0.1471 0.7471 0.0415
-7.750 0.2644 0.07805 0.07325 -0.1476 0.7417 0.0423
-7.500 0.2658 0.07608 0.07130 -0.1493 0.7367 0.0446
-7.250 0.2564 0.07411 0.06934 -0.1527 0.7323 0.0452
-7.000 0.2772 0.07131 0.06648 -0.1511 0.7287 0.0460
-6.750 0.2870 0.06948 0.06468 -0.1506 0.7236 0.0469
-6.500 0.2941 0.06755 0.06274 -0.1508 0.7191 0.0483
-6.250 0.2973 0.06573 0.06090 -0.1514 0.7154 0.0498
-6.000 0.2950 0.06294 0.05814 -0.1593 0.7110 0.0517
-5.750 0.3036 0.06008 0.05534 -0.1605 0.7065 0.0523
-5.500 0.3168 0.05866 0.05390 -0.1579 0.7029 0.0534
-5.250 0.3314 0.05660 0.05180 -0.1594 0.6996 0.0550
-5.000 0.3644 0.04845 0.04333 -0.1832 0.6965 0.0600
-4.750 0.3740 0.04739 0.04246 -0.1790 0.6925 0.0609
-4.500 0.3899 0.04608 0.04118 -0.1784 0.6888 0.0626
-4.250 0.4293 0.04071 0.03540 -0.1915 0.6855 0.0700
-4.000 0.4501 0.03917 0.03389 -0.1914 0.6828 0.0723
-3.750 0.4893 0.03593 0.03023 -0.1988 0.6805 0.0818
-3.500 0.5113 0.03462 0.02898 -0.1992 0.6772 0.0859
-3.250 0.5429 0.03251 0.02666 -0.2030 0.6738 0.0966
-3.000 0.5757 0.03083 0.02475 -0.2061 0.6708 0.1104
-2.750 0.6075 0.02941 0.02315 -0.2085 0.6681 0.1263
-2.500 0.6684 0.02317 0.01530 -0.2126 0.6661 0.0444
-2.250 0.7013 0.02193 0.01381 -0.2138 0.6640 0.0429
-2.000 0.7306 0.02139 0.01306 -0.2142 0.6613 0.0444
-1.750 0.7572 0.02089 0.01249 -0.2142 0.6583 0.0446
-1.500 0.7848 0.02040 0.01197 -0.2144 0.6555 0.0446
-1.250 0.8134 0.02002 0.01156 -0.2146 0.6530 0.0453
-1.000 0.8436 0.01956 0.01115 -0.2155 0.6508 0.0476
-0.750 0.8756 0.01926 0.01080 -0.2165 0.6488 0.0524
-0.500 0.9097 0.01891 0.01042 -0.2180 0.6468 0.0721
-0.250 0.9410 0.01836 0.01114 -0.2195 0.6444 0.5489
0.000 0.9623 0.01895 0.01180 -0.2183 0.6414 0.5930
0.250 0.9840 0.01942 0.01234 -0.2170 0.6388 0.6246
0.500 1.0065 0.01982 0.01278 -0.2159 0.6365 0.6539
0.750 1.0313 0.02009 0.01304 -0.2153 0.6346 0.6732
1.000 1.0596 0.02029 0.01315 -0.2157 0.6329 0.6830
1.250 1.0875 0.02046 0.01327 -0.2159 0.6314 0.6904
1.500 1.1175 0.02070 0.01340 -0.2167 0.6299 0.6976
1.750 1.1420 0.02113 0.01384 -0.2166 0.6281 0.7027
2.000 1.1610 0.02177 0.01456 -0.2157 0.6255 0.7094
2.250 1.1830 0.02231 0.01513 -0.2153 0.6229 0.7168
2.500 1.2064 0.02271 0.01555 -0.2150 0.6206 0.7227
2.750 1.2319 0.02308 0.01592 -0.2151 0.6186 0.7293
3.000 1.2584 0.02339 0.01624 -0.2153 0.6170 0.7358
3.250 1.2859 0.02367 0.01651 -0.2157 0.6156 0.7434
3.500 1.3142 0.02394 0.01677 -0.2162 0.6143 0.7521
3.750 1.3429 0.02427 0.01711 -0.2167 0.6131 0.7625
4.000 1.3545 0.02545 0.01844 -0.2150 0.6106 0.7725
4.250 1.3532 0.02730 0.02049 -0.2114 0.6067 0.7841
4.500 1.3618 0.02859 0.02190 -0.2093 0.6038 0.7991
4.750 1.3791 0.02927 0.02270 -0.2081 0.6017 0.8235
5.000 1.4010 0.02932 0.02292 -0.2073 0.6000 1.0000
5.250 1.4364 0.02925 0.02280 -0.2089 0.5986 1.0000
5.500 1.4740 0.02908 0.02257 -0.2107 0.5973 1.0000
5.750 1.5105 0.02911 0.02255 -0.2123 0.5961 1.0000
6.000 1.0995 0.06461 0.05874 -0.1735 0.5493 1.0000
6.250 1.1312 0.06448 0.05857 -0.1739 0.5485 1.0000
6.500 1.1657 0.06396 0.05802 -0.1742 0.5478 1.0000
6.750 1.2013 0.06328 0.05732 -0.1746 0.5473 1.0000
7.000 1.2389 0.06230 0.05633 -0.1751 0.5469 1.0000
7.250 1.1616 0.07300 0.06714 -0.1702 0.5273 1.0000
7.500 1.2062 0.07133 0.06545 -0.1708 0.5288 1.0000
7.750 1.2470 0.07002 0.06414 -0.1713 0.5296 1.0000
8.000 1.2864 0.06882 0.06296 -0.1718 0.5301 1.0000
8.250 1.2260 0.07795 0.07217 -0.1682 0.5119 1.0000
8.500 1.2679 0.07635 0.07060 -0.1685 0.5130 1.0000
8.750 1.3075 0.07498 0.06925 -0.1688 0.5137 1.0000
10.000 1.8555 0.03190 0.02625 -0.1959 0.5319 1.0000
11.250 1.8567 0.03576 0.03053 -0.1789 0.4956 1.0000
11.500 1.7020 0.05296 0.04797 -0.1666 0.4862 1.0000
11.750 1.8112 0.04242 0.03742 -0.1703 0.4777 1.0000
12.000 1.8113 0.04379 0.03882 -0.1679 0.4641 1.0000
12.250 1.7372 0.05439 0.04965 -0.1627 0.4577 1.0000
12.500 1.7077 0.06032 0.05568 -0.1602 0.4450 1.0000
12.750 1.6934 0.06457 0.06000 -0.1585 0.4294 1.0000
13.000 1.7303 0.06199 0.05731 -0.1580 0.3997 1.0000
13.250 1.7431 0.06187 0.05648 -0.1560 0.3286 1.0000
13.500 1.7198 0.06725 0.06161 -0.1539 0.2905 1.0000
13.750 1.6951 0.07317 0.06731 -0.1522 0.2567 1.0000
14.000 1.6698 0.07945 0.07338 -0.1509 0.2230 1.0000
14.250 1.6445 0.08600 0.07969 -0.1499 0.1869 1.0000
14.500 1.6192 0.09275 0.08618 -0.1492 0.1480 1.0000
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Polar data table (+)
Polar graphs
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