WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150A AIRFOIL (fx72150a-il) Reynolds number: 200,000 Max Cl/Cd: 78.36 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72150a-il-200000-n5.txt Download as CSV file: xf-fx72150a-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.1634 0.10241 0.09725 -0.1332 0.7332 0.0259
-10.250 0.1686 0.10009 0.09490 -0.1346 0.7287 0.0260
-10.000 0.1712 0.09783 0.09264 -0.1362 0.7237 0.0261
-9.750 0.1816 0.09514 0.08993 -0.1368 0.7188 0.0262
-9.500 0.1943 0.09263 0.08737 -0.1369 0.7145 0.0266
-9.250 0.2038 0.09037 0.08510 -0.1376 0.7099 0.0270
-9.000 0.2123 0.08815 0.08287 -0.1384 0.7050 0.0274
-8.750 0.2199 0.08590 0.08060 -0.1392 0.7005 0.0280
-8.250 0.2293 0.08129 0.07599 -0.1419 0.6922 0.0299
-8.000 0.2285 0.07869 0.07342 -0.1441 0.6878 0.0302
-7.750 0.2393 0.07644 0.07114 -0.1442 0.6838 0.0303
-7.500 0.2537 0.07461 0.06926 -0.1436 0.6803 0.0313
-7.250 0.2612 0.07252 0.06718 -0.1443 0.6764 0.0319
-7.000 0.2672 0.07034 0.06502 -0.1450 0.6723 0.0326
-6.750 0.2720 0.06815 0.06283 -0.1457 0.6686 0.0332
-6.500 0.2711 0.06578 0.06046 -0.1468 0.6651 0.0341
-6.250 0.2703 0.06298 0.05768 -0.1498 0.6617 0.0345
-6.000 0.2775 0.05953 0.05427 -0.1544 0.6577 0.0346
-5.750 0.2889 0.05761 0.05235 -0.1541 0.6539 0.0349
-5.500 0.3014 0.05563 0.05035 -0.1548 0.6504 0.0353
-5.250 0.3159 0.05304 0.04773 -0.1577 0.6473 0.0358
-4.750 0.3714 0.03750 0.03173 -0.1830 0.6412 0.0222
-4.250 0.4437 0.02760 0.02082 -0.1970 0.6351 0.0191
-4.000 0.4768 0.02536 0.01822 -0.2000 0.6324 0.0189
-3.750 0.5108 0.02334 0.01576 -0.2027 0.6300 0.0188
-3.500 0.5438 0.02166 0.01368 -0.2047 0.6273 0.0188
-3.250 0.5754 0.02036 0.01205 -0.2060 0.6244 0.0190
-3.000 0.6059 0.01937 0.01080 -0.2069 0.6216 0.0193
-2.750 0.6350 0.01880 0.01015 -0.2077 0.6190 0.0200
-2.500 0.6644 0.01834 0.00956 -0.2083 0.6166 0.0214
-2.250 0.6943 0.01783 0.00884 -0.2089 0.6144 0.0227
-2.000 0.7242 0.01737 0.00831 -0.2096 0.6125 0.0233
-1.750 0.7530 0.01701 0.00795 -0.2101 0.6100 0.0240
-1.500 0.7822 0.01672 0.00764 -0.2107 0.6075 0.0249
-1.250 0.8118 0.01649 0.00735 -0.2114 0.6050 0.0263
-1.000 0.8417 0.01629 0.00710 -0.2122 0.6026 0.0284
-0.750 0.8717 0.01613 0.00686 -0.2129 0.6003 0.0325
-0.500 0.9020 0.01597 0.00671 -0.2137 0.5983 0.0479
-0.250 0.9362 0.01532 0.00665 -0.2160 0.5966 0.2738
0.000 0.9647 0.01524 0.00708 -0.2165 0.5947 0.4956
0.250 0.9907 0.01549 0.00739 -0.2162 0.5926 0.5453
0.500 1.0166 0.01575 0.00766 -0.2159 0.5903 0.5785
0.750 1.0429 0.01593 0.00782 -0.2157 0.5880 0.5934
1.000 1.0697 0.01606 0.00791 -0.2157 0.5856 0.6005
1.250 1.0970 0.01619 0.00797 -0.2158 0.5835 0.6061
1.500 1.1250 0.01634 0.00803 -0.2161 0.5817 0.6127
1.750 1.1530 0.01648 0.00812 -0.2163 0.5801 0.6175
2.000 1.1804 0.01666 0.00827 -0.2165 0.5785 0.6222
2.250 1.2060 0.01687 0.00850 -0.2165 0.5767 0.6272
2.500 1.2318 0.01709 0.00874 -0.2164 0.5748 0.6319
2.750 1.2575 0.01730 0.00898 -0.2163 0.5730 0.6367
3.000 1.2835 0.01752 0.00922 -0.2163 0.5712 0.6428
3.250 1.3097 0.01773 0.00944 -0.2164 0.5696 0.6491
3.500 1.3360 0.01793 0.00966 -0.2164 0.5680 0.6547
3.750 1.3627 0.01813 0.00988 -0.2165 0.5664 0.6614
4.000 1.3900 0.01832 0.01007 -0.2168 0.5649 0.6680
4.250 1.4179 0.01852 0.01027 -0.2171 0.5635 0.6756
4.500 1.4429 0.01880 0.01063 -0.2170 0.5620 0.6842
4.750 1.4654 0.01914 0.01106 -0.2164 0.5602 0.6936
5.000 1.4882 0.01947 0.01149 -0.2159 0.5585 0.7043
5.250 1.5112 0.01979 0.01190 -0.2155 0.5568 0.7169
5.500 1.5344 0.02010 0.01232 -0.2151 0.5551 0.7313
6.000 1.5811 0.02061 0.01306 -0.2143 0.5520 0.7787
6.250 1.6015 0.02063 0.01329 -0.2131 0.5504 1.0000
6.500 1.6283 0.02090 0.01358 -0.2133 0.5488 1.0000
6.750 1.6566 0.02114 0.01382 -0.2138 0.5472 1.0000
7.000 1.6750 0.02166 0.01444 -0.2127 0.5450 1.0000
7.250 1.6894 0.02226 0.01519 -0.2109 0.5424 1.0000
7.500 1.7059 0.02281 0.01584 -0.2095 0.5399 1.0000
7.750 1.7244 0.02319 0.01629 -0.2083 0.5369 1.0000
8.000 1.7499 0.02319 0.01630 -0.2081 0.5330 1.0000
8.250 1.7678 0.02336 0.01651 -0.2067 0.5281 1.0000
8.500 1.7614 0.02415 0.01743 -0.2014 0.5224 1.0000
8.750 1.7757 0.02432 0.01763 -0.1994 0.5168 1.0000
9.000 1.7851 0.02478 0.01816 -0.1968 0.5115 1.0000
9.250 1.7781 0.02604 0.01957 -0.1922 0.5058 1.0000
9.500 1.7906 0.02648 0.02005 -0.1903 0.5002 1.0000
9.750 1.7867 0.02788 0.02157 -0.1866 0.4936 1.0000
10.000 1.7871 0.02909 0.02286 -0.1836 0.4857 1.0000
10.250 1.7860 0.03065 0.02452 -0.1807 0.4783 1.0000
10.500 1.7834 0.03247 0.02643 -0.1778 0.4704 1.0000
10.750 1.7775 0.03471 0.02879 -0.1749 0.4622 1.0000
11.000 1.7717 0.03705 0.03122 -0.1722 0.4519 1.0000
11.250 1.7451 0.04165 0.03599 -0.1685 0.4407 1.0000
11.500 1.7370 0.04465 0.03904 -0.1662 0.4254 1.0000
11.750 1.7415 0.04635 0.04066 -0.1645 0.4047 1.0000
12.000 1.7327 0.04947 0.04365 -0.1623 0.3698 1.0000
12.250 1.7172 0.05332 0.04720 -0.1597 0.3366 1.0000
12.500 1.6963 0.05822 0.05192 -0.1573 0.3039 1.0000
12.750 1.6733 0.06363 0.05715 -0.1552 0.2750 1.0000
13.000 1.6493 0.06945 0.06278 -0.1535 0.2422 1.0000
13.250 1.6264 0.07539 0.06853 -0.1521 0.2114 1.0000
13.500 1.6059 0.08124 0.07419 -0.1511 0.1792 1.0000
13.750 1.5876 0.08693 0.07969 -0.1503 0.1459 1.0000
14.000 1.5711 0.09253 0.08508 -0.1498 0.1136 1.0000
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Polar data table (+)
Polar graphs
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