P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 500,000 Max Cl/Cd: 74.06 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51dtip-il-500000.txt Download as CSV file: xf-p51dtip-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5030 0.11408 0.11133 -0.0229 0.8318 0.0177
-11.250 -0.5020 0.10960 0.10682 -0.0252 0.8291 0.0181
-11.000 -0.5015 0.10489 0.10213 -0.0277 0.8263 0.0186
-8.500 -0.6339 0.04626 0.04268 -0.0462 0.7973 0.0137
-8.250 -0.6389 0.04113 0.03724 -0.0442 0.7948 0.0133
-8.000 -0.6391 0.03574 0.03143 -0.0421 0.7925 0.0130
-7.750 -0.6322 0.03078 0.02592 -0.0399 0.7905 0.0134
-7.500 -0.6182 0.02730 0.02196 -0.0383 0.7886 0.0139
-7.250 -0.5988 0.02505 0.01933 -0.0372 0.7868 0.0143
-7.000 -0.5824 0.02059 0.01437 -0.0360 0.7849 0.0152
-6.750 -0.5581 0.01994 0.01369 -0.0359 0.7828 0.0163
-6.500 -0.5331 0.01922 0.01285 -0.0357 0.7807 0.0176
-6.250 -0.5075 0.01850 0.01200 -0.0355 0.7787 0.0194
-6.000 -0.4823 0.01766 0.01099 -0.0352 0.7770 0.0215
-5.750 -0.4582 0.01655 0.00982 -0.0349 0.7754 0.0241
-5.500 -0.4325 0.01606 0.00926 -0.0347 0.7739 0.0266
-5.250 -0.4058 0.01573 0.00887 -0.0347 0.7723 0.0291
-5.000 -0.3816 0.01467 0.00773 -0.0343 0.7706 0.0317
-4.750 -0.3574 0.01391 0.00696 -0.0340 0.7688 0.0342
-4.500 -0.3316 0.01352 0.00654 -0.0339 0.7671 0.0370
-4.250 -0.3061 0.01308 0.00604 -0.0337 0.7656 0.0390
-4.000 -0.2801 0.01272 0.00563 -0.0335 0.7641 0.0407
-3.750 -0.2549 0.01226 0.00511 -0.0333 0.7627 0.0427
-3.500 -0.2297 0.01180 0.00457 -0.0330 0.7613 0.0456
-3.250 -0.2033 0.01154 0.00428 -0.0329 0.7599 0.0489
-3.000 -0.1763 0.01131 0.00402 -0.0330 0.7585 0.0533
-2.750 -0.1505 0.01083 0.00373 -0.0330 0.7570 0.0918
-2.500 -0.1369 0.00853 0.00307 -0.0321 0.7553 0.5089
-2.250 -0.1134 0.00832 0.00336 -0.0313 0.7538 0.6787
-2.000 -0.0854 0.00847 0.00346 -0.0313 0.7525 0.7012
-1.750 -0.0577 0.00862 0.00362 -0.0312 0.7513 0.7177
-1.500 -0.0303 0.00882 0.00381 -0.0309 0.7501 0.7326
-1.250 -0.0027 0.00901 0.00399 -0.0308 0.7490 0.7448
-1.000 0.0243 0.00926 0.00426 -0.0304 0.7480 0.7583
-0.750 0.0511 0.00946 0.00452 -0.0299 0.7470 0.7686
-0.500 0.0795 0.00957 0.00456 -0.0301 0.7460 0.7726
-0.250 0.1077 0.00958 0.00460 -0.0304 0.7448 0.7751
0.000 0.1363 0.00961 0.00465 -0.0308 0.7436 0.7766
0.250 0.1649 0.00965 0.00470 -0.0312 0.7424 0.7782
0.500 0.1935 0.00971 0.00477 -0.0316 0.7412 0.7802
0.750 0.2222 0.00976 0.00483 -0.0320 0.7400 0.7821
1.000 0.2510 0.00978 0.00487 -0.0324 0.7385 0.7834
1.250 0.2798 0.00979 0.00488 -0.0328 0.7368 0.7845
1.500 0.3086 0.00980 0.00489 -0.0333 0.7353 0.7856
1.750 0.3373 0.00979 0.00488 -0.0336 0.7336 0.7866
2.000 0.3656 0.00972 0.00483 -0.0337 0.7302 0.7876
2.250 0.3937 0.00940 0.00454 -0.0336 0.7222 0.7887
2.500 0.4215 0.00890 0.00400 -0.0332 0.7092 0.7898
2.750 0.4495 0.00861 0.00371 -0.0330 0.6993 0.7911
3.000 0.4779 0.00850 0.00365 -0.0331 0.6934 0.7926
3.250 0.5061 0.00838 0.00358 -0.0332 0.6860 0.7942
3.500 0.5341 0.00819 0.00342 -0.0332 0.6736 0.7957
3.750 0.5620 0.00806 0.00334 -0.0332 0.6580 0.7973
4.000 0.5895 0.00796 0.00327 -0.0331 0.6310 0.7989
4.250 0.6001 0.00938 0.00363 -0.0306 0.3858 0.8008
4.500 0.6120 0.01088 0.00437 -0.0288 0.2097 0.8027
4.750 0.6256 0.01214 0.00501 -0.0272 0.0801 0.8047
5.000 0.6463 0.01277 0.00548 -0.0263 0.0498 0.8067
5.250 0.6684 0.01326 0.00596 -0.0256 0.0420 0.8089
5.500 0.6913 0.01367 0.00644 -0.0250 0.0378 0.8114
5.750 0.7133 0.01415 0.00694 -0.0243 0.0326 0.8140
6.000 0.7318 0.01487 0.00774 -0.0230 0.0280 0.8165
6.250 0.7530 0.01534 0.00827 -0.0221 0.0240 0.8189
6.500 0.7654 0.01667 0.00965 -0.0199 0.0201 0.8219
6.750 0.7896 0.01685 0.00990 -0.0195 0.0182 0.8249
7.000 0.8099 0.01747 0.01057 -0.0185 0.0164 0.8282
7.250 0.8293 0.01810 0.01124 -0.0174 0.0151 0.8313
7.500 0.8454 0.02004 0.01329 -0.0159 0.0138 0.8347
7.750 0.8683 0.02108 0.01446 -0.0152 0.0132 0.8384
8.000 0.8926 0.02246 0.01598 -0.0148 0.0127 0.8422
8.250 0.9163 0.02389 0.01760 -0.0142 0.0121 0.8461
8.500 0.9366 0.02457 0.01842 -0.0134 0.0112 0.8512
8.750 0.9571 0.02574 0.01973 -0.0127 0.0107 0.8569
9.000 0.9766 0.02749 0.02172 -0.0117 0.0104 0.8625
9.250 0.9933 0.02909 0.02351 -0.0106 0.0100 0.8698
9.500 1.0068 0.03167 0.02644 -0.0089 0.0099 0.8780
9.750 1.0145 0.03420 0.02928 -0.0067 0.0097 0.8903
16.000 0.7779 0.19020 0.18798 -0.0507 0.0137 1.0000
16.250 0.7839 0.19468 0.19246 -0.0531 0.0136 1.0000
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Polar data table (+)
Polar graphs
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