P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Reynolds number: 50,000 Max Cl/Cd: 28.02 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51droot-il-50000.txt Download as CSV file: xf-p51droot-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: P-51D ROOT (BL17.5) 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4218 0.10822 0.10050 -0.0357 1.0000 0.2387
-10.750 -0.5681 0.08094 0.07348 -0.0560 1.0000 0.1754
-10.500 -0.7273 0.07180 0.06426 -0.0547 1.0000 0.1614
-10.250 -0.7470 0.06860 0.06101 -0.0515 1.0000 0.1607
-10.000 -0.7707 0.06569 0.05801 -0.0476 1.0000 0.1601
-9.750 -0.7917 0.06282 0.05500 -0.0436 1.0000 0.1596
-9.500 -0.8099 0.05995 0.05196 -0.0397 1.0000 0.1592
-9.250 -0.8242 0.05714 0.04888 -0.0360 1.0000 0.1592
-9.000 -0.8331 0.05434 0.04581 -0.0325 1.0000 0.1594
-8.750 -0.8373 0.05163 0.04278 -0.0294 1.0000 0.1598
-8.500 -0.8383 0.04906 0.03985 -0.0264 1.0000 0.1605
-8.250 -0.8367 0.04668 0.03710 -0.0235 1.0000 0.1622
-8.000 -0.8207 0.04423 0.03475 -0.0223 1.0000 0.1665
-7.750 -0.8091 0.04228 0.03264 -0.0204 1.0000 0.1706
-7.500 -0.7980 0.04035 0.03041 -0.0184 1.0000 0.1742
-7.250 -0.7879 0.03872 0.02836 -0.0161 1.0000 0.1784
-7.000 -0.7681 0.03687 0.02669 -0.0152 1.0000 0.1856
-6.750 -0.7528 0.03549 0.02511 -0.0135 1.0000 0.1930
-6.500 -0.7325 0.03406 0.02382 -0.0123 1.0000 0.2023
-6.250 -0.7153 0.03292 0.02266 -0.0108 1.0000 0.2139
-6.000 -0.6992 0.03191 0.02174 -0.0090 1.0000 0.2284
-5.750 -0.6860 0.03091 0.02104 -0.0069 1.0000 0.2467
-5.500 -0.6784 0.02990 0.02038 -0.0043 1.0000 0.2711
-5.250 -0.6748 0.02864 0.01956 -0.0014 1.0000 0.3115
-5.000 -0.6783 0.02718 0.01944 0.0032 1.0000 0.4047
-4.750 -0.6803 0.02964 0.02272 0.0118 1.0000 0.5618
-4.500 -0.6754 0.03222 0.02523 0.0187 1.0000 0.6179
-4.250 -0.6595 0.03460 0.02749 0.0239 0.9967 0.6576
-4.000 -0.6252 0.03730 0.02999 0.0264 0.9859 0.6974
-3.750 -0.5768 0.04108 0.03362 0.0296 0.9769 0.7362
-3.500 -0.4820 0.04518 0.03737 0.0257 0.9703 0.7781
-3.250 -0.3716 0.04709 0.03886 0.0147 0.9641 0.8120
-3.000 -0.2622 0.04811 0.03953 0.0025 0.9583 0.8530
-2.750 -0.1943 0.04794 0.03913 -0.0055 0.9509 0.8765
-2.500 -0.1595 0.04766 0.03869 -0.0091 0.9424 0.8888
-2.250 -0.1172 0.04723 0.03814 -0.0139 0.9347 0.8986
-2.000 -0.0918 0.04706 0.03785 -0.0160 0.9275 0.9076
-1.750 -0.0599 0.04682 0.03751 -0.0190 0.9200 0.9159
-1.500 -0.0359 0.04672 0.03733 -0.0207 0.9131 0.9239
-1.250 -0.0030 0.04660 0.03713 -0.0240 0.9068 0.9315
-1.000 0.0029 0.04671 0.03720 -0.0225 0.9009 0.9384
-0.750 0.0463 0.04666 0.03707 -0.0277 0.8964 0.9458
-0.500 0.0536 0.04689 0.03727 -0.0265 0.8917 0.9521
-0.250 0.0732 0.04698 0.03733 -0.0277 0.8865 0.9578
0.000 0.0973 0.04721 0.03752 -0.0295 0.8823 0.9639
0.250 0.1217 0.04755 0.03784 -0.0314 0.8794 0.9691
0.500 0.1362 0.04790 0.03818 -0.0318 0.8767 0.9744
0.750 0.1414 0.04829 0.03857 -0.0307 0.8739 0.9795
1.000 0.1578 0.04869 0.03898 -0.0315 0.8713 0.9844
1.250 0.1739 0.04921 0.03950 -0.0324 0.8701 0.9896
1.500 0.1901 0.04980 0.04010 -0.0334 0.8691 0.9946
1.750 0.2147 0.05044 0.04076 -0.0358 0.8669 0.9999
2.000 0.2056 0.05096 0.04129 -0.0323 0.8679 1.0000
2.250 0.1927 0.05145 0.04179 -0.0283 0.8712 1.0000
2.500 0.1847 0.05193 0.04227 -0.0251 0.8744 1.0000
2.750 0.1846 0.05264 0.04300 -0.0233 0.8785 1.0000
5.750 0.2519 0.05916 0.04959 -0.0085 0.7919 1.0000
6.000 0.3106 0.05966 0.05017 -0.0115 0.7414 1.0000
6.250 0.3703 0.05980 0.05040 -0.0141 0.7009 1.0000
6.500 0.4124 0.05984 0.05054 -0.0147 0.6683 1.0000
6.750 0.4560 0.05985 0.05064 -0.0154 0.6407 1.0000
7.000 0.4878 0.06015 0.05105 -0.0153 0.6159 1.0000
7.250 0.5455 0.05916 0.05024 -0.0161 0.5930 1.0000
7.500 0.5567 0.06010 0.05124 -0.0145 0.5669 1.0000
7.750 0.6031 0.05886 0.05019 -0.0140 0.5430 1.0000
8.000 0.6738 0.05518 0.04677 -0.0133 0.5223 1.0000
8.250 0.6797 0.05599 0.04765 -0.0108 0.4935 1.0000
8.500 0.8369 0.04259 0.03476 -0.0104 0.4696 1.0000
8.750 0.8758 0.03923 0.03143 -0.0076 0.4332 1.0000
9.000 0.9283 0.03510 0.02710 -0.0058 0.3889 1.0000
9.250 0.9452 0.03470 0.02637 -0.0029 0.3522 1.0000
9.500 0.9780 0.03490 0.02590 -0.0020 0.3111 1.0000
9.750 1.0033 0.03679 0.02740 -0.0016 0.2759 1.0000
10.000 1.0371 0.03923 0.02948 -0.0025 0.2439 1.0000
10.250 1.0513 0.04145 0.03174 -0.0011 0.2244 1.0000
10.500 1.0701 0.04370 0.03400 -0.0003 0.2080 1.0000
10.750 1.0931 0.04603 0.03629 -0.0001 0.1941 1.0000
11.000 1.1014 0.04829 0.03874 0.0017 0.1846 1.0000
11.250 1.1137 0.05105 0.04163 0.0029 0.1768 1.0000
11.500 1.1158 0.05373 0.04455 0.0050 0.1710 1.0000
11.750 1.1382 0.05678 0.04759 0.0049 0.1638 1.0000
12.000 1.1180 0.05965 0.05081 0.0089 0.1619 1.0000
12.250 1.0960 0.06298 0.05443 0.0122 0.1605 1.0000
12.500 1.0702 0.06688 0.05860 0.0147 0.1598 1.0000
12.750 1.0378 0.07162 0.06358 0.0163 0.1599 1.0000
13.000 0.9973 0.07771 0.06988 0.0165 0.1609 1.0000
13.250 0.9525 0.08549 0.07783 0.0148 0.1626 1.0000
13.500 0.9103 0.09469 0.08713 0.0115 0.1643 1.0000
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Polar data table (+)
Polar graphs
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