B-29 ROOT AIRFOIL (b29root-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: B-29 ROOT AIRFOIL (b29root-il) Reynolds number: 50,000 Max Cl/Cd: 8.54 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b29root-il-50000-n5.txt Download as CSV file: xf-b29root-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: B-29 ROOT 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4150 0.11908 0.11048 -0.0553 1.0000 0.1240
-14.250 -0.5667 0.08834 0.07947 -0.0709 1.0000 0.1270
-14.000 -0.6653 0.07349 0.06422 -0.0769 1.0000 0.1273
-13.750 -0.7102 0.06695 0.05738 -0.0779 1.0000 0.1280
-13.500 -0.7077 0.06464 0.05508 -0.0774 1.0000 0.1297
-13.250 -0.7017 0.06283 0.05330 -0.0768 1.0000 0.1318
-13.000 -0.7071 0.06033 0.05074 -0.0759 1.0000 0.1338
-12.750 -0.7168 0.05777 0.04807 -0.0747 1.0000 0.1358
-12.500 -0.7291 0.05536 0.04554 -0.0729 1.0000 0.1378
-12.250 -0.7437 0.05326 0.04330 -0.0704 1.0000 0.1397
-12.000 -0.7562 0.05183 0.04180 -0.0672 1.0000 0.1415
-11.750 -0.7576 0.05147 0.04160 -0.0640 1.0000 0.1434
-11.500 -0.7373 0.05016 0.04029 -0.0649 0.9875 0.1471
-11.250 -0.7133 0.04821 0.03814 -0.0673 0.9734 0.1521
-11.000 -0.6800 0.04668 0.03656 -0.0701 0.9626 0.1578
-10.750 -0.6476 0.04528 0.03512 -0.0726 0.9515 0.1641
-10.500 -0.6164 0.04376 0.03349 -0.0752 0.9414 0.1714
-10.250 -0.5823 0.04243 0.03217 -0.0779 0.9323 0.1797
-10.000 -0.5543 0.04115 0.03086 -0.0797 0.9210 0.1884
-9.750 -0.5255 0.03972 0.02933 -0.0820 0.9121 0.1999
-9.500 -0.5045 0.03868 0.02842 -0.0825 0.8998 0.2105
-9.250 -0.4832 0.03754 0.02731 -0.0832 0.8896 0.2234
-9.000 -0.4677 0.03654 0.02635 -0.0828 0.8779 0.2380
-8.750 -0.4553 0.03567 0.02552 -0.0817 0.8669 0.2541
-8.500 -0.4439 0.03488 0.02479 -0.0803 0.8565 0.2726
-8.250 -0.4367 0.03430 0.02427 -0.0780 0.8457 0.2916
-8.000 -0.4280 0.03377 0.02377 -0.0757 0.8359 0.3130
-7.750 -0.4231 0.03342 0.02344 -0.0726 0.8257 0.3332
-7.500 -0.4166 0.03310 0.02312 -0.0695 0.8165 0.3541
-7.250 -0.4106 0.03289 0.02290 -0.0662 0.8078 0.3739
-7.000 -0.4065 0.03279 0.02280 -0.0625 0.7982 0.3920
-6.750 -0.3953 0.03262 0.02257 -0.0597 0.7915 0.4113
-6.500 -0.3973 0.03272 0.02266 -0.0550 0.7815 0.4264
-6.250 -0.3916 0.03263 0.02249 -0.0513 0.7740 0.4435
-6.000 -0.3777 0.03263 0.02245 -0.0488 0.7675 0.4606
-5.750 -0.3658 0.03290 0.02276 -0.0460 0.7585 0.4754
-5.500 -0.3479 0.03290 0.02272 -0.0440 0.7522 0.4919
-5.250 -0.3352 0.03292 0.02266 -0.0414 0.7460 0.5079
-5.000 -0.3319 0.03314 0.02287 -0.0374 0.7372 0.5224
-4.750 -0.3055 0.03332 0.02306 -0.0365 0.7314 0.5394
-4.500 -0.2751 0.03345 0.02313 -0.0361 0.7271 0.5575
-4.250 -0.2760 0.03393 0.02366 -0.0316 0.7175 0.5712
-4.000 -0.2658 0.03394 0.02361 -0.0285 0.7113 0.5875
-3.750 -0.2198 0.03414 0.02375 -0.0306 0.7072 0.6008
-3.500 -0.2157 0.03445 0.02407 -0.0271 0.6991 0.6122
-3.250 -0.1987 0.03463 0.02420 -0.0253 0.6923 0.6243
-3.000 -0.1645 0.03464 0.02414 -0.0261 0.6878 0.6354
-2.750 -0.1551 0.03451 0.02392 -0.0231 0.6828 0.6494
-2.500 -0.1336 0.03529 0.02476 -0.0223 0.6743 0.6582
-2.250 -0.1215 0.03524 0.02464 -0.0198 0.6688 0.6719
-2.000 -0.0720 0.03540 0.02472 -0.0228 0.6653 0.6817
-1.750 -0.0748 0.03595 0.02529 -0.0184 0.6575 0.6948
-1.500 -0.0535 0.03644 0.02577 -0.0175 0.6509 0.7062
-1.250 -0.0205 0.03655 0.02582 -0.0182 0.6466 0.7179
-1.000 0.0107 0.03648 0.02564 -0.0183 0.6435 0.7315
-0.750 0.0130 0.03782 0.02708 -0.0153 0.6341 0.7417
-0.500 0.0266 0.03812 0.02735 -0.0131 0.6286 0.7563
-0.250 0.0792 0.03837 0.02752 -0.0168 0.6252 0.7651
0.000 0.1146 0.03827 0.02732 -0.0176 0.6225 0.7779
0.250 0.0894 0.04017 0.02936 -0.0110 0.6113 0.7930
0.500 0.1332 0.04059 0.02972 -0.0137 0.6073 0.8022
0.750 0.1609 0.04058 0.02964 -0.0134 0.6041 0.8166
1.250 0.1864 0.04326 0.03237 -0.0111 0.5896 0.8401
1.500 0.2314 0.04358 0.03264 -0.0140 0.5863 0.8493
1.750 0.2722 0.04357 0.03257 -0.0159 0.5837 0.8603
2.250 0.2790 0.04683 0.03590 -0.0122 0.5680 0.8876
2.500 0.3186 0.04693 0.03596 -0.0142 0.5653 0.8986
2.750 0.3696 0.04683 0.03581 -0.0179 0.5633 0.9073
3.250 0.3654 0.05087 0.03995 -0.0146 0.5465 0.9364
3.500 0.4097 0.05071 0.03975 -0.0172 0.5445 0.9464
4.000 0.4251 0.05532 0.04446 -0.0191 0.5280 0.9710
4.250 0.4715 0.05519 0.04431 -0.0223 0.5258 0.9796
5.250 0.4651 0.06305 0.05220 -0.0188 0.4984 1.0000
5.500 0.4568 0.06430 0.05341 -0.0155 0.4929 1.0000
5.750 0.4663 0.06462 0.05368 -0.0133 0.4895 1.0000
6.000 0.4841 0.06457 0.05360 -0.0116 0.4871 1.0000
6.250 0.4358 0.06847 0.05747 -0.0063 0.4768 1.0000
6.500 0.4413 0.06934 0.05831 -0.0042 0.4727 1.0000
6.750 0.4575 0.06960 0.05854 -0.0026 0.4697 1.0000
7.250 0.4333 0.07393 0.06282 0.0028 0.4566 1.0000
7.500 0.4453 0.07469 0.06357 0.0043 0.4530 1.0000
7.750 0.4650 0.07501 0.06387 0.0055 0.4504 1.0000
8.000 0.4394 0.07836 0.06722 0.0082 0.4415 1.0000
8.250 0.4457 0.07967 0.06852 0.0097 0.4367 1.0000
8.500 0.4631 0.08026 0.06910 0.0108 0.4333 1.0000
9.000 0.4554 0.08453 0.07339 0.0139 0.4204 1.0000
9.250 0.4708 0.08534 0.07421 0.0150 0.4163 1.0000
9.500 0.4953 0.08547 0.07434 0.0159 0.4135 1.0000
9.750 0.4724 0.08913 0.07802 0.0174 0.4032 1.0000
10.000 0.4886 0.08986 0.07877 0.0184 0.3986 1.0000
10.250 0.5150 0.08979 0.07871 0.0192 0.3955 1.0000
10.500 0.4937 0.09350 0.08246 0.0204 0.3846 1.0000
10.750 0.5137 0.09389 0.08287 0.0213 0.3801 1.0000
11.250 0.5189 0.09766 0.08671 0.0230 0.3652 1.0000
11.500 0.5440 0.09755 0.08662 0.0239 0.3614 1.0000
11.750 0.5299 0.10105 0.09016 0.0245 0.3508 1.0000
12.000 0.5498 0.10135 0.09051 0.0253 0.3457 1.0000
12.250 0.5457 0.10406 0.09326 0.0258 0.3367 1.0000
12.500 0.5590 0.10497 0.09422 0.0265 0.3301 1.0000
12.750 0.5773 0.10537 0.09465 0.0274 0.3249 1.0000
13.000 0.5711 0.10834 0.09767 0.0276 0.3142 1.0000
13.250 0.5982 0.10762 0.09700 0.0286 0.3103 1.0000
13.500 0.5846 0.11156 0.10099 0.0285 0.2981 1.0000
13.750 0.6116 0.11072 0.10020 0.0296 0.2940 1.0000
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