P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 500,000 Max Cl/Cd: 63.73 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51dtip-il-500000-n5.txt Download as CSV file: xf-p51dtip-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5967 0.08263 0.07983 -0.0346 0.7785 0.0050
-10.750 -0.6313 0.06987 0.06707 -0.0446 0.7766 0.0048
-10.500 -0.7052 0.05652 0.05355 -0.0494 0.7737 0.0044
-10.250 -0.7531 0.04961 0.04641 -0.0465 0.7705 0.0044
-10.000 -0.8114 0.03666 0.03277 -0.0417 0.7680 0.0044
-9.750 -0.8215 0.03044 0.02593 -0.0388 0.7658 0.0045
-9.500 -0.8079 0.02843 0.02365 -0.0378 0.7639 0.0046
-9.250 -0.7922 0.02654 0.02150 -0.0369 0.7619 0.0049
-9.000 -0.7755 0.02456 0.01923 -0.0360 0.7597 0.0051
-8.750 -0.7567 0.02281 0.01722 -0.0352 0.7575 0.0054
-8.500 -0.7358 0.02148 0.01566 -0.0346 0.7554 0.0057
-8.250 -0.7131 0.02055 0.01455 -0.0342 0.7535 0.0062
-8.000 -0.6901 0.01961 0.01343 -0.0339 0.7518 0.0065
-7.750 -0.6667 0.01873 0.01237 -0.0335 0.7503 0.0068
-7.500 -0.6480 0.01666 0.00997 -0.0323 0.7487 0.0078
-7.250 -0.6249 0.01575 0.00889 -0.0318 0.7470 0.0091
-7.000 -0.6000 0.01526 0.00837 -0.0316 0.7452 0.0105
-6.750 -0.5748 0.01482 0.00787 -0.0314 0.7434 0.0121
-6.500 -0.5490 0.01450 0.00748 -0.0313 0.7416 0.0141
-6.250 -0.5233 0.01416 0.00709 -0.0312 0.7399 0.0156
-6.000 -0.4972 0.01388 0.00678 -0.0312 0.7382 0.0182
-5.750 -0.4711 0.01361 0.00644 -0.0311 0.7367 0.0206
-5.250 -0.4172 0.01329 0.00599 -0.0312 0.7339 0.0247
-5.000 -0.3918 0.01286 0.00555 -0.0311 0.7323 0.0269
-4.750 -0.3659 0.01250 0.00513 -0.0311 0.7308 0.0285
-4.500 -0.3396 0.01219 0.00478 -0.0311 0.7292 0.0298
-4.250 -0.3132 0.01191 0.00444 -0.0310 0.7278 0.0307
-4.000 -0.2866 0.01163 0.00412 -0.0310 0.7264 0.0315
-3.750 -0.2598 0.01139 0.00382 -0.0311 0.7251 0.0321
-3.500 -0.2329 0.01116 0.00355 -0.0311 0.7238 0.0327
-3.250 -0.2059 0.01095 0.00328 -0.0312 0.7226 0.0337
-2.750 -0.1515 0.01054 0.00282 -0.0313 0.7200 0.0376
-2.500 -0.1239 0.01037 0.00265 -0.0315 0.7185 0.0409
-2.250 -0.0968 0.01012 0.00248 -0.0316 0.7171 0.0605
-2.000 -0.0721 0.00947 0.00227 -0.0316 0.7158 0.1797
-1.750 -0.0490 0.00853 0.00200 -0.0316 0.7145 0.3737
-1.500 -0.0289 0.00747 0.00193 -0.0308 0.7132 0.6552
-1.250 -0.0008 0.00752 0.00200 -0.0308 0.7121 0.6819
-1.000 0.0273 0.00758 0.00207 -0.0309 0.7110 0.6980
-0.750 0.0559 0.00764 0.00208 -0.0311 0.7100 0.7070
-0.500 0.0843 0.00767 0.00212 -0.0313 0.7090 0.7127
-0.250 0.1129 0.00774 0.00215 -0.0316 0.7081 0.7200
0.000 0.1410 0.00780 0.00224 -0.0316 0.7072 0.7273
0.250 0.1696 0.00786 0.00230 -0.0319 0.7060 0.7331
0.500 0.1984 0.00787 0.00233 -0.0323 0.7047 0.7349
0.750 0.2271 0.00788 0.00237 -0.0326 0.7034 0.7363
1.000 0.2558 0.00789 0.00241 -0.0329 0.7018 0.7374
1.250 0.2845 0.00789 0.00243 -0.0333 0.6998 0.7384
1.500 0.3131 0.00785 0.00238 -0.0335 0.6959 0.7394
1.750 0.3415 0.00779 0.00235 -0.0337 0.6900 0.7404
2.000 0.3698 0.00771 0.00228 -0.0338 0.6819 0.7416
2.250 0.3980 0.00763 0.00223 -0.0339 0.6713 0.7430
2.500 0.4261 0.00757 0.00216 -0.0340 0.6568 0.7444
2.750 0.4539 0.00754 0.00212 -0.0341 0.6387 0.7458
3.000 0.4818 0.00756 0.00214 -0.0342 0.6166 0.7470
3.250 0.4981 0.00866 0.00241 -0.0326 0.4170 0.7484
3.500 0.5176 0.00960 0.00293 -0.0318 0.3056 0.7496
3.750 0.5374 0.01046 0.00336 -0.0310 0.2009 0.7510
4.000 0.5596 0.01104 0.00373 -0.0305 0.1398 0.7524
4.250 0.5821 0.01156 0.00406 -0.0300 0.0938 0.7539
4.500 0.6043 0.01210 0.00443 -0.0294 0.0526 0.7555
4.750 0.6280 0.01248 0.00476 -0.0290 0.0408 0.7572
5.000 0.6525 0.01279 0.00510 -0.0287 0.0365 0.7590
5.250 0.6762 0.01316 0.00546 -0.0283 0.0322 0.7610
5.500 0.7004 0.01345 0.00582 -0.0280 0.0290 0.7628
5.750 0.7240 0.01376 0.00618 -0.0275 0.0261 0.7647
6.000 0.7467 0.01415 0.00661 -0.0269 0.0234 0.7666
6.250 0.7711 0.01438 0.00691 -0.0266 0.0203 0.7687
6.500 0.7935 0.01477 0.00728 -0.0260 0.0141 0.7709
6.750 0.8153 0.01520 0.00775 -0.0253 0.0115 0.7733
7.000 0.8363 0.01571 0.00827 -0.0244 0.0096 0.7757
7.250 0.8556 0.01633 0.00897 -0.0233 0.0082 0.7780
7.500 0.8713 0.01726 0.01005 -0.0215 0.0072 0.7807
7.750 0.8857 0.01834 0.01127 -0.0196 0.0068 0.7837
8.000 0.9057 0.01885 0.01185 -0.0187 0.0064 0.7869
8.250 0.9241 0.01945 0.01252 -0.0175 0.0060 0.7901
8.500 0.9407 0.02012 0.01338 -0.0160 0.0055 0.7935
8.750 0.9565 0.02102 0.01441 -0.0145 0.0053 0.7975
9.000 0.9729 0.02200 0.01552 -0.0131 0.0050 0.8019
9.250 0.9898 0.02279 0.01642 -0.0118 0.0047 0.8064
9.500 1.0059 0.02381 0.01759 -0.0105 0.0045 0.8113
9.750 1.0217 0.02481 0.01872 -0.0092 0.0044 0.8168
10.000 1.0362 0.02594 0.02001 -0.0079 0.0042 0.8225
10.250 1.0491 0.02733 0.02158 -0.0064 0.0040 0.8292
10.500 1.0572 0.02954 0.02409 -0.0044 0.0038 0.8365
10.750 1.0645 0.03156 0.02638 -0.0025 0.0037 0.8457
11.000 1.0599 0.03511 0.03037 0.0004 0.0036 0.8571
11.500 1.0545 0.04043 0.03643 0.0047 0.0035 0.9132
11.750 1.0531 0.04395 0.04030 0.0048 0.0035 1.0000
12.000 1.0398 0.04778 0.04437 0.0064 0.0035 1.0000
12.250 1.0247 0.05193 0.04876 0.0075 0.0035 1.0000
12.500 1.0086 0.05637 0.05342 0.0079 0.0035 1.0000
12.750 0.9850 0.06205 0.05931 0.0075 0.0035 1.0000
13.000 0.9636 0.06797 0.06542 0.0060 0.0035 1.0000
13.250 0.9409 0.07490 0.07252 0.0030 0.0035 1.0000
13.500 0.9153 0.08418 0.08198 -0.0024 0.0035 1.0000
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Polar data table (+)
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