P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Reynolds number: 100,000 Max Cl/Cd: 46.24 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51droot-il-100000.txt Download as CSV file: xf-p51droot-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6381 0.08317 0.07763 -0.0645 1.0000 0.1016
-12.250 -0.6440 0.07793 0.07237 -0.0657 1.0000 0.1005
-12.000 -0.6697 0.07189 0.06626 -0.0675 1.0000 0.0988
-11.750 -0.7081 0.06622 0.06046 -0.0685 1.0000 0.0971
-11.500 -0.7479 0.06189 0.05597 -0.0672 1.0000 0.0957
-11.250 -0.8686 0.05946 0.05299 -0.0540 1.0000 0.0904
-11.000 -0.8900 0.05762 0.05094 -0.0488 1.0000 0.0901
-10.750 -0.9026 0.05505 0.04818 -0.0448 1.0000 0.0903
-10.500 -0.9112 0.05243 0.04536 -0.0412 1.0000 0.0905
-10.250 -0.9155 0.04986 0.04260 -0.0378 1.0000 0.0908
-10.000 -0.9159 0.04738 0.03992 -0.0348 1.0000 0.0913
-9.750 -0.9135 0.04506 0.03740 -0.0320 1.0000 0.0917
-9.500 -0.9052 0.04313 0.03535 -0.0298 1.0000 0.0929
-9.250 -0.8961 0.04147 0.03358 -0.0277 1.0000 0.0944
-9.000 -0.8879 0.03983 0.03178 -0.0253 1.0000 0.0963
-8.750 -0.8791 0.03812 0.02982 -0.0229 1.0000 0.0980
-8.500 -0.8685 0.03642 0.02785 -0.0207 1.0000 0.0995
-8.250 -0.8566 0.03492 0.02605 -0.0185 1.0000 0.1011
-8.000 -0.8423 0.03333 0.02429 -0.0168 1.0000 0.1034
-7.750 -0.8253 0.03207 0.02311 -0.0156 1.0000 0.1064
-7.500 -0.8099 0.03110 0.02208 -0.0140 1.0000 0.1096
-7.250 -0.7942 0.03016 0.02103 -0.0124 1.0000 0.1128
-7.000 -0.7739 0.02924 0.01995 -0.0116 0.9987 0.1165
-6.750 -0.7267 0.02808 0.01897 -0.0160 0.9908 0.1245
-6.500 -0.6790 0.02699 0.01788 -0.0202 0.9825 0.1336
-6.250 -0.6347 0.02619 0.01709 -0.0239 0.9725 0.1461
-6.000 -0.5936 0.02508 0.01623 -0.0270 0.9628 0.1635
-5.750 -0.5537 0.02375 0.01524 -0.0301 0.9534 0.1961
-5.500 -0.5308 0.02143 0.01393 -0.0313 0.9407 0.2950
-5.250 -0.5082 0.02122 0.01509 -0.0297 0.9265 0.5303
-5.000 -0.4697 0.02246 0.01620 -0.0302 0.9133 0.5813
-4.750 -0.4321 0.02346 0.01704 -0.0307 0.9011 0.6103
-4.500 -0.3804 0.02462 0.01815 -0.0329 0.8956 0.6314
-4.250 -0.3489 0.02542 0.01890 -0.0319 0.8828 0.6487
-4.000 -0.3110 0.02670 0.02016 -0.0308 0.8732 0.6679
-3.750 -0.2697 0.02770 0.02113 -0.0303 0.8655 0.6853
-3.500 -0.2459 0.02787 0.02121 -0.0287 0.8531 0.6996
-3.250 -0.1996 0.02834 0.02160 -0.0296 0.8477 0.7089
-3.000 -0.1802 0.02827 0.02145 -0.0277 0.8353 0.7196
-2.750 -0.1469 0.02808 0.02115 -0.0279 0.8299 0.7311
-2.500 -0.1186 0.02849 0.02153 -0.0265 0.8191 0.7400
-2.250 -0.0929 0.02804 0.02098 -0.0260 0.8136 0.7522
-2.000 -0.0635 0.02830 0.02121 -0.0253 0.8039 0.7589
-1.750 -0.0506 0.02740 0.02019 -0.0240 0.7978 0.7685
-1.500 -0.0248 0.02742 0.02019 -0.0233 0.7888 0.7725
-1.250 0.0062 0.02709 0.01978 -0.0237 0.7837 0.7779
-1.000 0.0112 0.02662 0.01923 -0.0214 0.7762 0.7865
-0.750 0.0412 0.02660 0.01920 -0.0214 0.7704 0.7906
-0.500 0.0720 0.02633 0.01887 -0.0219 0.7667 0.7961
-0.250 0.0766 0.02614 0.01863 -0.0196 0.7598 0.8037
0.000 0.1021 0.02613 0.01862 -0.0193 0.7542 0.8075
0.250 0.1326 0.02588 0.01832 -0.0198 0.7506 0.8116
0.500 0.1554 0.02568 0.01808 -0.0196 0.7468 0.8167
0.750 0.1546 0.02605 0.01847 -0.0168 0.7392 0.8225
1.000 0.1814 0.02605 0.01848 -0.0170 0.7357 0.8258
1.250 0.2107 0.02596 0.01837 -0.0175 0.7331 0.8299
1.500 0.2116 0.02665 0.01909 -0.0150 0.7265 0.8353
1.750 0.2215 0.02707 0.01952 -0.0136 0.7210 0.8403
2.000 0.2471 0.02722 0.01970 -0.0136 0.7182 0.8441
2.250 0.2769 0.02724 0.01972 -0.0144 0.7161 0.8483
2.500 0.2457 0.02940 0.02194 -0.0088 0.7068 0.8556
2.750 0.2680 0.02964 0.02221 -0.0085 0.7024 0.8600
3.000 0.3110 0.02908 0.02168 -0.0102 0.6999 0.8641
3.250 0.3630 0.02816 0.02076 -0.0130 0.6979 0.8679
3.500 0.3068 0.03145 0.02413 -0.0047 0.6852 0.8773
3.750 0.3626 0.03043 0.02317 -0.0078 0.6827 0.8810
4.000 0.4005 0.03004 0.02281 -0.0089 0.6785 0.8867
4.250 0.3961 0.03126 0.02410 -0.0057 0.6674 0.8953
4.500 0.4954 0.02784 0.02070 -0.0122 0.6642 0.8960
4.750 0.4811 0.02947 0.02242 -0.0079 0.6523 0.9070
5.000 0.5622 0.02695 0.01993 -0.0130 0.6474 0.9087
5.250 0.5695 0.02774 0.02083 -0.0108 0.6370 0.9192
5.500 0.6273 0.02642 0.01956 -0.0138 0.6304 0.9242
5.750 0.6525 0.02670 0.01998 -0.0139 0.6208 0.9341
6.000 0.7044 0.02582 0.01916 -0.0167 0.6126 0.9401
6.250 0.7401 0.02577 0.01926 -0.0183 0.6006 0.9490
6.500 0.7920 0.02490 0.01844 -0.0212 0.5890 0.9552
6.750 0.8454 0.02398 0.01754 -0.0245 0.5736 0.9611
7.000 0.8861 0.02329 0.01698 -0.0265 0.5509 0.9711
7.250 0.9342 0.02208 0.01577 -0.0291 0.5236 0.9804
7.500 0.9757 0.02119 0.01496 -0.0316 0.4880 0.9945
7.750 0.9606 0.02090 0.01474 -0.0256 0.4667 1.0000
8.000 0.9571 0.02070 0.01448 -0.0209 0.4254 1.0000
8.250 0.9562 0.02086 0.01417 -0.0163 0.3568 1.0000
8.500 0.9485 0.02188 0.01458 -0.0112 0.3117 1.0000
8.750 0.9457 0.02324 0.01553 -0.0073 0.2815 1.0000
9.000 0.9503 0.02459 0.01661 -0.0046 0.2571 1.0000
9.250 0.9578 0.02585 0.01771 -0.0023 0.2352 1.0000
9.500 0.9657 0.02707 0.01880 -0.0003 0.2158 1.0000
9.750 0.9734 0.02832 0.01989 0.0017 0.1978 1.0000
10.000 0.9834 0.02965 0.02100 0.0034 0.1805 1.0000
10.250 0.9947 0.03106 0.02228 0.0049 0.1641 1.0000
10.500 1.0118 0.03255 0.02358 0.0057 0.1493 1.0000
10.750 1.0250 0.03392 0.02501 0.0070 0.1381 1.0000
11.000 1.0433 0.03543 0.02653 0.0077 0.1280 1.0000
11.250 1.0715 0.03696 0.02786 0.0074 0.1194 1.0000
11.500 1.0829 0.03841 0.02953 0.0088 0.1134 1.0000
11.750 1.1159 0.04001 0.03090 0.0079 0.1067 1.0000
12.000 1.1235 0.04160 0.03280 0.0096 0.1029 1.0000
12.250 1.1386 0.04329 0.03462 0.0105 0.0991 1.0000
12.500 1.1716 0.04508 0.03625 0.0095 0.0947 1.0000
12.750 1.1744 0.04718 0.03866 0.0114 0.0924 1.0000
13.000 1.1770 0.04936 0.04111 0.0131 0.0901 1.0000
13.250 1.1833 0.05161 0.04357 0.0144 0.0879 1.0000
13.500 1.1906 0.05380 0.04589 0.0154 0.0860 1.0000
13.750 1.2136 0.05604 0.04805 0.0151 0.0833 1.0000
14.000 1.2060 0.05923 0.05151 0.0168 0.0823 1.0000
14.250 1.1874 0.06252 0.05514 0.0187 0.0816 1.0000
14.500 1.1685 0.06633 0.05926 0.0198 0.0811 1.0000
14.750 1.1474 0.07069 0.06391 0.0204 0.0808 1.0000
15.000 1.1214 0.07579 0.06930 0.0201 0.0807 1.0000
15.250 1.0921 0.08170 0.07546 0.0190 0.0808 1.0000
15.500 1.0591 0.08855 0.08256 0.0169 0.0812 1.0000
15.750 1.0221 0.09663 0.09085 0.0136 0.0817 1.0000
16.000 0.9852 0.10577 0.10017 0.0092 0.0823 1.0000
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