P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 50,000 Max Cl/Cd: 22.64 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51dtip-il-50000.txt Download as CSV file: xf-p51dtip-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: P-51D TIP (BL215) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4622 0.11232 0.10595 -0.0148 1.0000 0.3004
-9.750 -0.4622 0.10949 0.10318 -0.0152 1.0000 0.3187
-9.500 -0.4677 0.10696 0.10075 -0.0156 1.0000 0.3356
-9.250 -0.4445 0.10268 0.09644 -0.0145 1.0000 0.3607
-9.000 -0.4343 0.09951 0.09329 -0.0135 1.0000 0.3896
-8.750 -0.4194 0.09586 0.08966 -0.0127 1.0000 0.4153
-8.250 -0.4147 0.09084 0.08472 -0.0108 1.0000 0.4645
-8.000 -0.3912 0.08649 0.08035 -0.0109 1.0000 0.4831
-7.750 -0.3778 0.08362 0.07749 -0.0097 1.0000 0.5118
-6.750 -0.5346 0.07772 0.07236 0.0003 1.0000 0.4232
-6.500 -0.5786 0.07672 0.07153 0.0052 1.0000 0.4219
-6.250 -0.6439 0.07138 0.06630 0.0013 1.0000 0.3772
-6.000 -0.6740 0.05597 0.04928 -0.0188 1.0000 0.1738
-5.750 -0.6615 0.05095 0.04346 -0.0184 1.0000 0.1466
-5.500 -0.6474 0.04732 0.03896 -0.0172 1.0000 0.1359
-5.250 -0.6309 0.04407 0.03532 -0.0160 1.0000 0.1350
-5.000 -0.6116 0.04093 0.03177 -0.0149 1.0000 0.1321
-4.750 -0.5897 0.03811 0.02841 -0.0138 1.0000 0.1292
-4.500 -0.5674 0.03592 0.02577 -0.0127 1.0000 0.1319
-4.250 -0.5441 0.03422 0.02347 -0.0115 1.0000 0.1365
-4.000 -0.5198 0.03215 0.02124 -0.0106 1.0000 0.1393
-3.750 -0.4953 0.03065 0.01960 -0.0094 1.0000 0.1445
-3.500 -0.4719 0.02951 0.01840 -0.0080 1.0000 0.1559
-3.250 -0.1706 0.02963 0.02083 -0.0320 1.0000 1.0000
-3.000 -0.1654 0.02950 0.02047 -0.0296 1.0000 1.0000
-2.750 -0.1597 0.02938 0.02014 -0.0273 1.0000 1.0000
-2.500 -0.1537 0.02927 0.01981 -0.0249 1.0000 1.0000
-2.250 -0.1475 0.02915 0.01952 -0.0226 1.0000 1.0000
-2.000 -0.1411 0.02905 0.01926 -0.0202 1.0000 1.0000
-1.750 -0.1345 0.02894 0.01901 -0.0179 1.0000 1.0000
-1.500 -0.1279 0.02884 0.01877 -0.0155 1.0000 1.0000
-1.250 -0.1213 0.02873 0.01854 -0.0132 1.0000 1.0000
-1.000 -0.1147 0.02862 0.01831 -0.0108 1.0000 1.0000
-0.750 -0.1082 0.02850 0.01806 -0.0084 1.0000 1.0000
-0.500 -0.1019 0.02837 0.01784 -0.0060 1.0000 1.0000
-0.250 -0.0957 0.02824 0.01762 -0.0035 1.0000 1.0000
0.000 -0.0899 0.02808 0.01740 -0.0010 1.0000 1.0000
0.250 -0.0843 0.02791 0.01716 0.0016 1.0000 1.0000
0.500 -0.0790 0.02772 0.01691 0.0042 1.0000 1.0000
0.750 -0.0738 0.02751 0.01663 0.0069 1.0000 1.0000
1.000 -0.0684 0.02729 0.01637 0.0094 1.0000 1.0000
1.250 -0.0622 0.02709 0.01612 0.0119 1.0000 1.0000
1.500 -0.0539 0.02695 0.01594 0.0139 1.0000 1.0000
1.750 -0.0420 0.02695 0.01589 0.0153 1.0000 1.0000
2.000 -0.0269 0.02707 0.01597 0.0161 1.0000 1.0000
2.250 -0.0095 0.02730 0.01617 0.0164 1.0000 1.0000
2.500 0.0093 0.02762 0.01647 0.0165 1.0000 1.0000
2.750 0.0291 0.02800 0.01684 0.0164 1.0000 1.0000
3.000 0.0494 0.02845 0.01730 0.0162 1.0000 1.0000
3.250 0.0701 0.02896 0.01783 0.0159 1.0000 1.0000
3.500 0.0909 0.02952 0.01844 0.0156 1.0000 1.0000
3.750 0.1117 0.03013 0.01911 0.0152 1.0000 1.0000
4.000 0.1323 0.03080 0.01984 0.0148 1.0000 1.0000
4.250 0.1527 0.03153 0.02065 0.0144 1.0000 1.0000
4.500 0.1727 0.03231 0.02156 0.0139 1.0000 1.0000
4.750 0.1923 0.03316 0.02252 0.0135 1.0000 1.0000
5.000 0.2114 0.03409 0.02359 0.0130 1.0000 1.0000
5.250 0.2297 0.03512 0.02476 0.0125 1.0000 1.0000
5.500 0.2472 0.03625 0.02606 0.0119 1.0000 1.0000
5.750 0.2636 0.03753 0.02756 0.0112 1.0000 1.0000
6.000 0.4576 0.04316 0.03446 -0.0159 0.8504 1.0000
6.250 0.6294 0.02970 0.02297 -0.0110 0.5732 1.0000
6.500 0.6668 0.03000 0.01940 -0.0008 0.1747 1.0000
6.750 0.7411 0.03273 0.02192 -0.0044 0.1340 1.0000
7.000 0.7875 0.03596 0.02510 -0.0061 0.1175 1.0000
7.250 0.8168 0.03870 0.02843 -0.0055 0.1107 1.0000
7.500 0.8440 0.04215 0.03195 -0.0055 0.1035 1.0000
7.750 0.8661 0.04574 0.03606 -0.0044 0.1029 1.0000
8.000 0.8859 0.04982 0.04053 -0.0034 0.1036 1.0000
8.250 0.9005 0.05393 0.04505 -0.0021 0.1039 1.0000
8.500 0.9113 0.05809 0.04959 -0.0007 0.1041 1.0000
8.750 0.9003 0.06147 0.05397 0.0027 0.1108 1.0000
9.000 0.8998 0.06601 0.05883 0.0041 0.1140 1.0000
9.250 0.8980 0.07066 0.06381 0.0054 0.1205 1.0000
9.500 0.8807 0.07586 0.06931 0.0065 0.1289 1.0000
9.750 0.8454 0.08042 0.07413 0.0075 0.1391 1.0000
10.000 0.8090 0.08672 0.08054 0.0056 0.1528 1.0000
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Polar data table (+)
Polar graphs
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