PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 500,000 Max Cl/Cd: 79.01 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pmc19sm-il-500000.txt Download as CSV file: xf-pmc19sm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6167 0.09308 0.09109 0.0207 1.0000 0.0139
-8.250 -0.6192 0.08786 0.08588 0.0154 1.0000 0.0140
-8.000 -0.6228 0.08327 0.08126 0.0114 1.0000 0.0141
-7.750 -0.6205 0.07903 0.07699 0.0088 1.0000 0.0142
-7.500 -0.6161 0.07492 0.07283 0.0067 1.0000 0.0144
-7.250 -0.6095 0.07091 0.06875 0.0049 1.0000 0.0146
-7.000 -0.6005 0.06698 0.06474 0.0034 1.0000 0.0149
-6.750 -0.5893 0.06313 0.06079 0.0021 1.0000 0.0154
-6.500 -0.5759 0.05934 0.05689 0.0012 1.0000 0.0159
-6.250 -0.5600 0.05562 0.05304 0.0004 1.0000 0.0167
-6.000 -0.5315 0.05323 0.05036 0.0006 1.0000 0.0187
-5.750 -0.5099 0.05029 0.04723 0.0007 1.0000 0.0189
-4.250 -0.3756 0.03059 0.02638 -0.0013 0.8844 0.0250
-4.000 -0.3472 0.03074 0.02615 0.0007 0.8427 0.0268
-3.750 -0.3232 0.02870 0.02376 0.0018 0.8119 0.0269
-3.500 -0.3014 0.02349 0.01802 0.0028 0.7882 0.0277
-3.250 -0.2774 0.02094 0.01524 0.0032 0.7636 0.0289
-3.000 -0.2502 0.01785 0.01177 0.0044 0.7421 0.0235
-2.750 -0.2229 0.01630 0.00994 0.0051 0.7196 0.0247
-2.500 -0.1956 0.01495 0.00831 0.0058 0.6980 0.0256
-2.250 -0.1681 0.01422 0.00738 0.0062 0.6765 0.0267
-1.750 -0.1162 0.01204 0.00497 0.0071 0.6364 0.0317
-1.500 -0.0892 0.01165 0.00449 0.0074 0.6163 0.0344
-1.250 -0.0624 0.01122 0.00393 0.0076 0.5978 0.0362
-1.000 -0.0347 0.01108 0.00370 0.0077 0.5788 0.0379
-0.750 -0.0087 0.01027 0.00277 0.0079 0.5609 0.0425
-0.500 0.0189 0.01006 0.00247 0.0080 0.5432 0.0466
-0.250 0.0469 0.00993 0.00223 0.0080 0.5264 0.0507
0.000 0.0747 0.00969 0.00193 0.0079 0.5101 0.0607
0.250 0.1027 0.00955 0.00175 0.0079 0.4940 0.0782
0.500 0.1227 0.00743 0.00152 0.0083 0.4802 0.7090
0.750 0.1481 0.00738 0.00162 0.0091 0.4660 0.7768
1.000 0.1749 0.00744 0.00167 0.0095 0.4526 0.8042
1.250 0.2015 0.00751 0.00173 0.0099 0.4396 0.8236
1.500 0.2279 0.00760 0.00180 0.0103 0.4270 0.8444
1.750 0.2537 0.00767 0.00187 0.0110 0.4151 0.8626
2.000 0.2795 0.00773 0.00194 0.0116 0.4043 0.8779
2.250 0.3066 0.00782 0.00199 0.0118 0.3942 0.8880
2.500 0.3335 0.00789 0.00204 0.0120 0.3844 0.8951
2.750 0.3609 0.00796 0.00209 0.0120 0.3746 0.9034
3.000 0.3876 0.00802 0.00215 0.0123 0.3660 0.9115
3.250 0.4144 0.00811 0.00221 0.0125 0.3579 0.9206
4.000 0.4966 0.00828 0.00245 0.0127 0.3350 0.9560
4.250 0.5305 0.00843 0.00260 0.0113 0.3279 0.9695
4.500 0.5681 0.00853 0.00274 0.0090 0.3199 0.9910
4.750 0.5979 0.00867 0.00286 0.0082 0.3098 1.0000
5.000 0.6263 0.00886 0.00300 0.0078 0.2999 1.0000
5.250 0.6549 0.00897 0.00313 0.0074 0.2887 1.0000
5.500 0.6834 0.00911 0.00330 0.0071 0.2791 1.0000
5.750 0.7116 0.00928 0.00346 0.0068 0.2678 1.0000
6.000 0.7396 0.00945 0.00363 0.0065 0.2525 1.0000
6.250 0.7672 0.00971 0.00383 0.0062 0.2274 1.0000
6.500 0.7919 0.01069 0.00433 0.0060 0.1332 1.0000
6.750 0.8135 0.01255 0.00570 0.0059 0.0353 1.0000
7.000 0.8387 0.01352 0.00676 0.0059 0.0277 1.0000
7.250 0.8650 0.01403 0.00735 0.0059 0.0250 1.0000
7.500 0.8905 0.01471 0.00812 0.0058 0.0223 1.0000
7.750 0.9133 0.01600 0.00953 0.0060 0.0200 1.0000
8.000 0.9347 0.01741 0.01109 0.0063 0.0190 1.0000
8.250 0.9583 0.01828 0.01205 0.0065 0.0183 1.0000
8.500 0.9812 0.01923 0.01309 0.0067 0.0172 1.0000
8.750 1.0039 0.02012 0.01406 0.0069 0.0160 1.0000
9.000 1.0252 0.02121 0.01523 0.0072 0.0151 1.0000
9.250 1.0449 0.02249 0.01658 0.0075 0.0144 1.0000
9.500 1.0616 0.02431 0.01847 0.0082 0.0137 1.0000
9.750 1.0734 0.02754 0.02181 0.0095 0.0132 1.0000
10.000 1.0904 0.02945 0.02391 0.0102 0.0127 1.0000
10.250 1.1095 0.03042 0.02503 0.0106 0.0121 1.0000
10.500 1.1257 0.03199 0.02676 0.0112 0.0114 1.0000
10.750 1.1386 0.03421 0.02919 0.0119 0.0110 1.0000
11.000 1.1484 0.03668 0.03187 0.0128 0.0108 1.0000
11.250 1.1546 0.03935 0.03475 0.0136 0.0105 1.0000
11.500 1.1540 0.04216 0.03777 0.0147 0.0104 1.0000
11.750 1.1486 0.04540 0.04122 0.0149 0.0103 1.0000
12.000 1.1397 0.04944 0.04550 0.0141 0.0103 1.0000
12.250 1.1266 0.05442 0.05071 0.0122 0.0104 1.0000
12.500 1.1104 0.06013 0.05666 0.0093 0.0105 1.0000
12.750 1.0913 0.06660 0.06335 0.0056 0.0107 1.0000
13.000 1.0723 0.07333 0.07027 0.0014 0.0109 1.0000
13.250 1.0520 0.08060 0.07770 -0.0033 0.0110 1.0000
13.500 1.0314 0.08821 0.08546 -0.0083 0.0112 1.0000
13.750 1.0109 0.09609 0.09347 -0.0133 0.0114 1.0000
14.000 0.9899 0.10453 0.10203 -0.0187 0.0115 1.0000
14.250 0.9689 0.11362 0.11123 -0.0244 0.0117 1.0000
14.500 0.9475 0.12350 0.12120 -0.0304 0.0120 1.0000
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Polar data table (+)
Polar graphs
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