PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 50,000 Max Cl/Cd: 32.31 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pmc19sm-il-50000-n5.txt Download as CSV file: xf-pmc19sm-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6018 0.09996 0.09382 0.0133 1.0000 0.0912
-8.000 -0.6145 0.09662 0.09043 0.0072 1.0000 0.0928
-7.750 -0.6231 0.09404 0.08767 0.0029 1.0000 0.0935
-7.500 -0.6007 0.08692 0.08081 0.0058 1.0000 0.0970
-7.250 -0.5946 0.08293 0.07680 0.0046 1.0000 0.1017
-6.750 -0.5846 0.07483 0.06858 0.0012 1.0000 0.1139
-6.500 -0.5794 0.07111 0.06465 -0.0007 1.0000 0.1242
-6.250 -0.5707 0.06737 0.06080 -0.0017 1.0000 0.1378
-5.750 -0.5479 0.05947 0.05284 -0.0022 1.0000 0.1721
-5.500 -0.5371 0.05554 0.04885 -0.0024 1.0000 0.1966
-5.250 -0.4821 0.05223 0.04430 -0.0046 1.0000 0.0816
-5.000 -0.4553 0.04821 0.03994 -0.0042 1.0000 0.0605
-4.750 -0.4322 0.04490 0.03630 -0.0041 1.0000 0.0568
-4.500 -0.4067 0.04197 0.03291 -0.0037 1.0000 0.0539
-4.250 -0.3829 0.03941 0.03007 -0.0037 1.0000 0.0558
-4.000 -0.3576 0.03711 0.02748 -0.0035 1.0000 0.0582
-3.750 -0.3309 0.03479 0.02483 -0.0032 1.0000 0.0583
-3.500 -0.3033 0.03258 0.02231 -0.0028 1.0000 0.0578
-3.250 -0.2754 0.03057 0.02004 -0.0025 1.0000 0.0582
-3.000 -0.2475 0.02893 0.01815 -0.0022 1.0000 0.0614
-2.750 -0.2192 0.02771 0.01655 -0.0018 1.0000 0.0650
-2.500 -0.1917 0.02587 0.01478 -0.0016 1.0000 0.0667
-2.250 -0.1607 0.02447 0.01343 -0.0019 0.9819 0.0694
-2.000 -0.1151 0.02340 0.01216 -0.0046 0.9318 0.0781
-1.750 -0.0775 0.02229 0.01092 -0.0060 0.8915 0.0844
-1.500 -0.0483 0.02160 0.00997 -0.0058 0.8552 0.0905
-1.250 -0.0244 0.02103 0.00923 -0.0049 0.8226 0.1029
-1.000 -0.0012 0.02051 0.00850 -0.0037 0.7937 0.1159
-0.750 0.0223 0.02000 0.00781 -0.0026 0.7673 0.1356
-0.500 0.0296 0.01759 0.00769 0.0018 0.7460 0.6792
-0.250 0.0398 0.01774 0.00804 0.0088 0.7247 0.8423
0.000 0.1523 0.01798 0.00780 -0.0023 0.6900 0.9989
0.250 0.1747 0.01801 0.00755 -0.0017 0.6683 1.0000
0.500 0.1958 0.01805 0.00738 -0.0009 0.6476 1.0000
0.750 0.2167 0.01812 0.00724 0.0001 0.6291 1.0000
1.000 0.2379 0.01822 0.00716 0.0008 0.6106 1.0000
1.250 0.2591 0.01834 0.00713 0.0017 0.5933 1.0000
1.500 0.2804 0.01849 0.00714 0.0025 0.5772 1.0000
1.750 0.3018 0.01866 0.00719 0.0033 0.5619 1.0000
2.000 0.3235 0.01887 0.00729 0.0041 0.5474 1.0000
2.250 0.3459 0.01911 0.00745 0.0048 0.5336 1.0000
2.500 0.3689 0.01938 0.00764 0.0053 0.5203 1.0000
2.750 0.3927 0.01969 0.00786 0.0058 0.5077 1.0000
3.000 0.4170 0.02001 0.00813 0.0061 0.4960 1.0000
3.250 0.4418 0.02036 0.00843 0.0065 0.4850 1.0000
3.500 0.4676 0.02076 0.00885 0.0065 0.4732 1.0000
3.750 0.4934 0.02120 0.00931 0.0065 0.4622 1.0000
4.000 0.5192 0.02164 0.00977 0.0066 0.4523 1.0000
4.250 0.5451 0.02209 0.01022 0.0067 0.4430 1.0000
4.500 0.5712 0.02264 0.01094 0.0066 0.4330 1.0000
4.750 0.5972 0.02318 0.01154 0.0066 0.4243 1.0000
5.000 0.6232 0.02373 0.01220 0.0066 0.4157 1.0000
5.250 0.6492 0.02441 0.01304 0.0065 0.4070 1.0000
5.500 0.6752 0.02497 0.01373 0.0066 0.3999 1.0000
5.750 0.7009 0.02578 0.01481 0.0064 0.3910 1.0000
6.000 0.7269 0.02639 0.01553 0.0066 0.3848 1.0000
6.250 0.7521 0.02735 0.01683 0.0062 0.3762 1.0000
6.500 0.7780 0.02804 0.01773 0.0064 0.3703 1.0000
6.750 0.8025 0.02902 0.01909 0.0062 0.3611 1.0000
7.000 0.8269 0.02856 0.01866 0.0074 0.3422 1.0000
7.250 0.8494 0.02793 0.01814 0.0085 0.3142 1.0000
7.500 0.8716 0.02772 0.01819 0.0091 0.2855 1.0000
7.750 0.8923 0.02762 0.01838 0.0095 0.2308 1.0000
8.000 0.9052 0.02951 0.01952 0.0094 0.1041 1.0000
8.250 0.9133 0.03287 0.02251 0.0091 0.0761 1.0000
8.500 0.9222 0.03576 0.02543 0.0089 0.0655 1.0000
8.750 0.9284 0.03865 0.02840 0.0087 0.0601 1.0000
9.000 0.9354 0.04122 0.03118 0.0088 0.0568 1.0000
9.250 0.9399 0.04391 0.03401 0.0088 0.0542 1.0000
9.500 0.9411 0.04674 0.03692 0.0088 0.0519 1.0000
9.750 0.9418 0.04966 0.03985 0.0088 0.0496 1.0000
10.000 0.9479 0.05226 0.04270 0.0087 0.0471 1.0000
10.250 0.9541 0.05488 0.04558 0.0088 0.0447 1.0000
10.500 0.9629 0.05728 0.04815 0.0097 0.0431 1.0000
10.750 0.9732 0.05969 0.05073 0.0107 0.0418 1.0000
11.000 0.9836 0.06232 0.05354 0.0118 0.0407 1.0000
11.250 0.9926 0.06535 0.05676 0.0125 0.0398 1.0000
11.500 1.0000 0.06896 0.06051 0.0131 0.0387 1.0000
11.750 0.9953 0.07350 0.06526 0.0116 0.0382 1.0000
12.000 0.9853 0.07855 0.07057 0.0087 0.0380 1.0000
12.250 0.9738 0.08410 0.07635 0.0054 0.0379 1.0000
12.500 0.9610 0.09012 0.08257 0.0018 0.0379 1.0000
12.750 0.9471 0.09663 0.08924 -0.0022 0.0379 1.0000
13.000 0.9330 0.10347 0.09623 -0.0064 0.0381 1.0000
13.250 0.9189 0.11067 0.10355 -0.0107 0.0382 1.0000
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Polar data table (+)
Polar graphs
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