P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 100,000 Max Cl/Cd: 40.82 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51dtip-il-100000.txt Download as CSV file: xf-p51dtip-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5151 0.09505 0.09086 -0.0428 1.0000 0.1081
-9.500 -0.4907 0.09193 0.08773 -0.0385 1.0000 0.1157
-9.250 -0.5015 0.08727 0.08315 -0.0439 1.0000 0.1202
-9.000 -0.5269 0.08321 0.07919 -0.0484 1.0000 0.1212
-8.750 -0.5541 0.08238 0.07845 -0.0442 1.0000 0.1207
-8.500 -0.5789 0.08097 0.07707 -0.0411 0.9980 0.1201
-8.250 -0.6100 0.07701 0.07267 -0.0497 0.9837 0.1226
-8.000 -0.5842 0.07190 0.06772 -0.0502 0.9818 0.1354
-7.750 -0.4923 0.05595 0.05204 -0.0553 0.9711 0.1624
-7.500 -0.5682 0.06364 0.05930 -0.0529 0.9718 0.1548
-7.250 -0.5571 0.06008 0.05564 -0.0542 0.9681 0.1698
-6.000 -0.5005 0.03789 0.03023 -0.0503 0.9458 0.0798
-5.750 -0.4770 0.03430 0.02631 -0.0500 0.9438 0.0767
-5.500 -0.4497 0.03176 0.02328 -0.0499 0.9420 0.0766
-5.250 -0.4327 0.03068 0.02175 -0.0479 0.9396 0.0800
-5.000 -0.4169 0.02944 0.02017 -0.0456 0.9370 0.0808
-4.750 -0.3936 0.02736 0.01803 -0.0449 0.9349 0.0838
-4.500 -0.3700 0.02637 0.01696 -0.0445 0.9328 0.0904
-4.250 -0.3444 0.02545 0.01588 -0.0439 0.9312 0.0938
-4.000 -0.3207 0.02437 0.01486 -0.0433 0.9300 0.0979
-3.750 -0.2987 0.02378 0.01430 -0.0426 0.9287 0.1071
-3.500 -0.2789 0.02312 0.01374 -0.0416 0.9276 0.1171
-3.250 -0.2689 0.02273 0.01335 -0.0387 0.9261 0.1281
-3.000 -0.2600 0.02212 0.01296 -0.0357 0.9244 0.1602
-2.750 -0.2752 0.02030 0.01371 -0.0276 0.9234 0.6795
-2.500 -0.0461 0.02541 0.01843 -0.0443 0.9294 0.9375
-2.250 0.0129 0.02510 0.01791 -0.0511 0.9293 0.9493
-2.000 0.0523 0.02497 0.01761 -0.0544 0.9284 0.9571
-1.750 0.0945 0.02482 0.01733 -0.0584 0.9275 0.9634
-1.500 0.0827 0.02527 0.01777 -0.0524 0.9247 0.9695
-1.250 0.0988 0.02537 0.01782 -0.0517 0.9235 0.9735
-1.000 0.1053 0.02562 0.01802 -0.0493 0.9224 0.9768
-0.750 0.1077 0.02588 0.01825 -0.0460 0.9208 0.9786
-0.500 0.1102 0.02616 0.01850 -0.0428 0.9199 0.9806
-0.250 0.1139 0.02642 0.01875 -0.0399 0.9199 0.9828
0.000 0.1232 0.02663 0.01894 -0.0381 0.9199 0.9845
0.250 0.1373 0.02684 0.01914 -0.0371 0.9195 0.9868
0.500 0.1486 0.02710 0.01940 -0.0357 0.9202 0.9896
0.750 0.1575 0.02739 0.01969 -0.0339 0.9215 0.9923
1.000 0.1713 0.02767 0.01998 -0.0330 0.9218 0.9949
1.250 0.1901 0.02800 0.02032 -0.0331 0.9229 0.9983
1.500 0.1999 0.02836 0.02070 -0.0316 0.9248 1.0000
1.750 0.2006 0.02868 0.02104 -0.0283 0.9264 1.0000
2.000 0.1589 0.02836 0.02072 -0.0177 0.9349 1.0000
2.250 0.1519 0.02840 0.02077 -0.0131 0.9381 1.0000
2.500 0.1492 0.02832 0.02073 -0.0091 0.9368 1.0000
2.750 0.1809 0.02886 0.02131 -0.0109 0.9243 1.0000
3.000 0.1827 0.02888 0.02134 -0.0077 0.9215 1.0000
3.250 0.1925 0.02918 0.02168 -0.0062 0.9212 1.0000
3.500 0.2269 0.02996 0.02252 -0.0084 0.9102 1.0000
3.750 0.2641 0.03073 0.02342 -0.0110 0.8973 1.0000
4.000 0.2981 0.03120 0.02400 -0.0126 0.8793 1.0000
4.250 0.3650 0.03157 0.02458 -0.0180 0.8465 1.0000
4.500 0.4150 0.03161 0.02486 -0.0207 0.8215 1.0000
4.750 0.7289 0.01796 0.01233 -0.0425 0.6733 1.0000
5.000 0.7099 0.01739 0.01003 -0.0311 0.3132 1.0000
5.250 0.6867 0.01940 0.01100 -0.0237 0.1747 1.0000
5.500 0.6761 0.02049 0.01166 -0.0177 0.1329 1.0000
5.750 0.6703 0.02118 0.01220 -0.0124 0.1157 1.0000
6.000 0.6730 0.02210 0.01299 -0.0086 0.1037 1.0000
6.250 0.6888 0.02329 0.01407 -0.0070 0.0895 1.0000
6.500 0.7158 0.02510 0.01568 -0.0069 0.0776 1.0000
6.750 0.7426 0.02637 0.01708 -0.0067 0.0678 1.0000
7.000 0.7799 0.02913 0.01990 -0.0076 0.0624 1.0000
7.250 0.8078 0.03097 0.02197 -0.0076 0.0565 1.0000
7.500 0.8371 0.03380 0.02499 -0.0079 0.0541 1.0000
7.750 0.8636 0.03713 0.02872 -0.0074 0.0541 1.0000
8.000 0.8821 0.04126 0.03368 -0.0054 0.0576 1.0000
8.250 0.8967 0.04553 0.03846 -0.0038 0.0599 1.0000
8.500 0.9080 0.04982 0.04312 -0.0023 0.0618 1.0000
8.750 0.8579 0.04536 0.03981 0.0048 0.0744 1.0000
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Polar data table (+)
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