PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 50,000 Max Cl/Cd: 27.96 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pmc19sm-il-50000.txt Download as CSV file: xf-pmc19sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: PMC19 Smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6224 0.10784 0.10183 0.0217 1.0000 0.1627
-8.250 -0.6082 0.10313 0.09714 0.0239 1.0000 0.1734
-8.000 -0.6291 0.09937 0.09349 0.0161 1.0000 0.1771
-7.750 -0.6205 0.09489 0.08907 0.0170 1.0000 0.1903
-7.500 -0.6191 0.09070 0.08492 0.0160 1.0000 0.2043
-7.250 -0.6257 0.08676 0.08100 0.0130 1.0000 0.2199
-6.500 -0.4906 0.08388 0.07805 0.0585 1.0000 0.5853
-6.250 -0.4363 0.08048 0.07459 0.0638 1.0000 0.7163
-6.000 -0.3521 0.07236 0.06635 0.0592 1.0000 0.8568
-4.500 -0.4973 0.05393 0.04883 0.0447 1.0000 0.5596
-4.250 -0.4791 0.03890 0.03293 0.0077 1.0000 0.4151
-4.000 -0.4198 0.03495 0.02733 -0.0038 1.0000 0.3031
-3.750 -0.3751 0.03361 0.02510 -0.0056 1.0000 0.2454
-3.500 -0.3352 0.03244 0.02326 -0.0057 1.0000 0.2016
-3.250 -0.2995 0.03107 0.02138 -0.0052 1.0000 0.1727
-3.000 -0.2669 0.02947 0.01943 -0.0048 1.0000 0.1559
-2.750 -0.2367 0.02805 0.01765 -0.0043 1.0000 0.1517
-2.500 -0.2078 0.02691 0.01624 -0.0038 1.0000 0.1498
-2.250 -0.1804 0.02531 0.01466 -0.0033 1.0000 0.1476
-2.000 -0.1572 0.02422 0.01361 -0.0023 1.0000 0.1473
-1.750 -0.1403 0.02352 0.01293 -0.0009 1.0000 0.1510
-1.500 -0.1269 0.02294 0.01245 0.0003 1.0000 0.1589
-1.250 -0.1117 0.02278 0.01216 0.0008 0.9986 0.1635
-1.000 -0.0398 0.02113 0.01055 -0.0083 0.9688 0.1868
-0.750 0.0964 0.01831 0.01021 -0.0169 0.9664 1.0000
-0.500 0.1703 0.01831 0.00962 -0.0260 0.9176 1.0000
-0.250 0.2013 0.01866 0.00966 -0.0265 0.8739 1.0000
0.000 0.2196 0.01909 0.00985 -0.0247 0.8385 1.0000
0.250 0.2364 0.01950 0.01007 -0.0226 0.8082 1.0000
0.500 0.2534 0.01988 0.01028 -0.0207 0.7818 1.0000
0.750 0.2706 0.02026 0.01050 -0.0187 0.7585 1.0000
1.000 0.2891 0.02068 0.01081 -0.0174 0.7355 1.0000
1.250 0.3066 0.02107 0.01107 -0.0155 0.7161 1.0000
1.500 0.3254 0.02155 0.01145 -0.0142 0.6971 1.0000
1.750 0.3446 0.02206 0.01188 -0.0131 0.6790 1.0000
2.000 0.3638 0.02259 0.01232 -0.0118 0.6625 1.0000
2.250 0.3836 0.02316 0.01285 -0.0107 0.6472 1.0000
2.500 0.4044 0.02379 0.01341 -0.0098 0.6325 1.0000
2.750 0.4262 0.02448 0.01407 -0.0092 0.6185 1.0000
3.000 0.4490 0.02525 0.01482 -0.0089 0.6051 1.0000
3.250 0.4723 0.02608 0.01569 -0.0086 0.5922 1.0000
3.500 0.4960 0.02695 0.01657 -0.0085 0.5804 1.0000
3.750 0.5199 0.02771 0.01732 -0.0079 0.5700 1.0000
4.000 0.5441 0.02878 0.01847 -0.0082 0.5583 1.0000
4.250 0.5682 0.03012 0.01994 -0.0090 0.5471 1.0000
4.500 0.5920 0.03143 0.02140 -0.0095 0.5370 1.0000
4.750 0.6164 0.03233 0.02235 -0.0089 0.5284 1.0000
5.000 0.6389 0.03435 0.02460 -0.0107 0.5180 1.0000
5.250 0.6614 0.03610 0.02652 -0.0115 0.5092 1.0000
5.500 0.6845 0.03756 0.02811 -0.0117 0.5010 1.0000
5.750 0.7030 0.04050 0.03136 -0.0141 0.4924 1.0000
6.000 0.7268 0.04167 0.03267 -0.0134 0.4856 1.0000
6.250 0.7379 0.04608 0.03737 -0.0176 0.4775 1.0000
6.500 0.7606 0.04765 0.03911 -0.0172 0.4715 1.0000
6.750 0.7620 0.05335 0.04503 -0.0224 0.4653 1.0000
7.000 0.7658 0.05823 0.05006 -0.0261 0.4618 1.0000
7.250 0.7896 0.05982 0.05187 -0.0251 0.4559 1.0000
7.500 0.7801 0.06626 0.05838 -0.0304 0.4549 1.0000
7.750 0.7742 0.07151 0.06369 -0.0338 0.4549 1.0000
8.000 0.7650 0.07623 0.06847 -0.0359 0.4544 1.0000
8.250 0.7558 0.08061 0.07288 -0.0376 0.4527 1.0000
8.500 0.9413 0.03366 0.02426 0.0128 0.1240 1.0000
8.750 0.9562 0.03604 0.02659 0.0141 0.1125 1.0000
9.000 0.9729 0.03841 0.02906 0.0153 0.1035 1.0000
9.250 0.9909 0.04092 0.03152 0.0165 0.0959 1.0000
9.500 1.0114 0.04368 0.03461 0.0176 0.0917 1.0000
9.750 1.0318 0.04688 0.03804 0.0185 0.0892 1.0000
10.000 1.0490 0.05063 0.04208 0.0192 0.0879 1.0000
10.250 1.0609 0.05486 0.04665 0.0196 0.0871 1.0000
10.500 1.0684 0.05973 0.05174 0.0197 0.0860 1.0000
10.750 1.0637 0.06430 0.05676 0.0196 0.0858 1.0000
11.000 1.0541 0.06912 0.06192 0.0190 0.0858 1.0000
11.250 0.9821 0.07743 0.07086 0.0111 0.0917 1.0000
11.500 0.9436 0.08732 0.08086 0.0028 0.0941 1.0000
11.750 0.9147 0.09734 0.09085 -0.0041 0.0962 1.0000
12.000 0.8996 0.10560 0.09908 -0.0084 0.0977 1.0000
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Polar data table (+)
Polar graphs
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