B-29 ROOT AIRFOIL (b29root-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: B-29 ROOT AIRFOIL (b29root-il) Reynolds number: 100,000 Max Cl/Cd: 13.81 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b29root-il-100000.txt Download as CSV file: xf-b29root-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3152 0.12064 0.11502 -0.0477 1.0000 0.1929
-12.750 -0.3086 0.11929 0.11374 -0.0473 1.0000 0.2056
-12.500 -1.0385 0.05087 0.04332 -0.0427 0.9991 0.1304
-12.250 -0.9972 0.04866 0.04107 -0.0472 0.9918 0.1333
-12.000 -0.9731 0.04645 0.03863 -0.0493 0.9819 0.1358
-11.750 -0.9565 0.04444 0.03632 -0.0502 0.9712 0.1382
-11.500 -0.9447 0.04273 0.03419 -0.0499 0.9606 0.1407
-11.250 -0.8902 0.04024 0.03179 -0.0558 0.9556 0.1448
-11.000 -0.8466 0.03840 0.02984 -0.0600 0.9501 0.1492
-10.750 -0.8195 0.03692 0.02809 -0.0613 0.9412 0.1533
-10.500 -0.7605 0.03482 0.02609 -0.0676 0.9370 0.1595
-10.250 -0.7145 0.03324 0.02440 -0.0718 0.9318 0.1662
-10.000 -0.6713 0.03177 0.02297 -0.0752 0.9236 0.1732
-9.750 -0.6321 0.03054 0.02171 -0.0780 0.9159 0.1819
-9.500 -0.5889 0.02927 0.02057 -0.0813 0.9086 0.1917
-9.250 -0.5617 0.02834 0.01961 -0.0818 0.8983 0.2021
-9.000 -0.5359 0.02751 0.01884 -0.0821 0.8890 0.2145
-8.750 -0.5161 0.02678 0.01826 -0.0813 0.8786 0.2275
-8.500 -0.5018 0.02616 0.01775 -0.0795 0.8692 0.2428
-8.250 -0.4942 0.02566 0.01736 -0.0765 0.8586 0.2598
-8.000 -0.4898 0.02522 0.01703 -0.0728 0.8494 0.2806
-7.750 -0.4919 0.02494 0.01683 -0.0680 0.8390 0.3035
-7.500 -0.4912 0.02468 0.01673 -0.0632 0.8315 0.3295
-7.250 -0.5008 0.02487 0.01703 -0.0568 0.8206 0.3514
-7.000 -0.5010 0.02484 0.01702 -0.0514 0.8135 0.3779
-6.750 -0.5065 0.02517 0.01740 -0.0456 0.8038 0.3985
-6.500 -0.5034 0.02530 0.01751 -0.0409 0.7961 0.4203
-6.250 -0.4920 0.02532 0.01748 -0.0374 0.7910 0.4422
-6.000 -0.4906 0.02582 0.01810 -0.0330 0.7807 0.4575
-5.750 -0.4744 0.02587 0.01816 -0.0304 0.7743 0.4761
-5.500 -0.4516 0.02586 0.01812 -0.0288 0.7699 0.4949
-5.250 -0.4577 0.02643 0.01871 -0.0234 0.7594 0.5072
-5.000 -0.4420 0.02647 0.01870 -0.0209 0.7536 0.5241
-4.750 -0.4099 0.02640 0.01865 -0.0208 0.7495 0.5412
-4.500 -0.4090 0.02703 0.01936 -0.0166 0.7395 0.5525
-4.250 -0.3951 0.02707 0.01935 -0.0139 0.7334 0.5677
-4.000 -0.3630 0.02701 0.01928 -0.0139 0.7295 0.5838
-3.750 -0.3519 0.02757 0.01992 -0.0113 0.7220 0.5959
-3.500 -0.3512 0.02792 0.02024 -0.0068 0.7139 0.6093
-3.250 -0.3176 0.02784 0.02016 -0.0070 0.7098 0.6263
-3.000 -0.2781 0.02785 0.02020 -0.0079 0.7067 0.6456
-2.750 -0.2963 0.02918 0.02167 -0.0013 0.6954 0.6566
-2.500 -0.2725 0.02938 0.02188 0.0000 0.6905 0.6746
-2.250 -0.2404 0.02919 0.02163 0.0002 0.6873 0.6919
-2.000 -0.1790 0.02910 0.02153 -0.0047 0.6849 0.7047
-1.750 -0.2302 0.03080 0.02337 0.0066 0.6713 0.7165
-1.500 -0.2000 0.03073 0.02326 0.0068 0.6678 0.7325
-1.250 -0.1273 0.03069 0.02319 0.0001 0.6659 0.7440
-1.000 -0.1910 0.03281 0.02546 0.0129 0.6529 0.7586
-0.750 -0.1657 0.03292 0.02553 0.0137 0.6484 0.7754
-0.500 -0.0701 0.03296 0.02554 0.0034 0.6467 0.7840
-0.250 -0.0183 0.03281 0.02530 0.0004 0.6447 0.7979
0.000 -0.1268 0.03648 0.02920 0.0184 0.6292 0.8181
0.250 -0.0129 0.03648 0.02910 0.0054 0.6278 0.8226
0.500 0.0845 0.03628 0.02879 -0.0048 0.6262 0.8274
0.750 0.1442 0.03592 0.02834 -0.0090 0.6244 0.8383
1.000 0.2384 0.03580 0.02810 -0.0191 0.6230 0.8402
1.250 0.1498 0.04076 0.03332 -0.0055 0.6075 0.8612
1.500 0.2427 0.04016 0.03262 -0.0147 0.6060 0.8643
1.750 0.2912 0.03954 0.03191 -0.0170 0.6043 0.8765
2.000 0.3785 0.03887 0.03114 -0.0258 0.6030 0.8792
2.250 0.2788 0.04540 0.03793 -0.0128 0.5864 0.9020
2.500 0.3627 0.04430 0.03676 -0.0204 0.5853 0.9079
2.750 0.4305 0.04324 0.03563 -0.0256 0.5841 0.9157
3.000 0.5140 0.04202 0.03433 -0.0336 0.5831 0.9198
3.250 0.3816 0.05059 0.04314 -0.0190 0.5651 0.9489
3.500 0.4766 0.04869 0.04120 -0.0276 0.5645 0.9517
3.750 0.5655 0.04687 0.03933 -0.0357 0.5639 0.9560
4.000 0.6298 0.04559 0.03800 -0.0404 0.5631 0.9641
4.250 0.4328 0.06184 0.05457 -0.0298 0.5363 0.9925
4.500 0.4645 0.06366 0.05642 -0.0344 0.5311 1.0000
4.750 0.4751 0.06364 0.05635 -0.0324 0.5280 1.0000
5.000 0.5050 0.06268 0.05534 -0.0315 0.5259 1.0000
5.250 0.5375 0.06179 0.05441 -0.0309 0.5241 1.0000
5.500 0.3797 0.07092 0.06355 -0.0183 0.5146 1.0000
5.750 0.3806 0.07174 0.06433 -0.0157 0.5108 1.0000
6.000 0.4148 0.07094 0.06349 -0.0149 0.5074 1.0000
6.250 0.4625 0.06969 0.06220 -0.0150 0.5052 1.0000
6.500 0.3645 0.07652 0.06903 -0.0077 0.5016 1.0000
6.750 0.3409 0.07932 0.07181 -0.0046 0.4997 1.0000
7.000 0.3314 0.08184 0.07433 -0.0026 0.5005 1.0000
7.250 0.3344 0.08418 0.07665 -0.0013 0.5026 1.0000
7.500 0.3420 0.08642 0.07889 -0.0004 0.5039 1.0000
7.750 0.3624 0.08852 0.08099 -0.0002 0.5050 1.0000
8.000 0.3720 0.08741 0.07984 0.0026 0.4876 1.0000
8.250 0.3726 0.08997 0.08240 0.0037 0.4873 1.0000
8.500 0.3741 0.09259 0.08503 0.0048 0.4859 1.0000
8.750 0.3737 0.09174 0.08414 0.0079 0.4652 1.0000
9.000 0.3645 0.09470 0.08712 0.0091 0.4648 1.0000
9.250 0.3703 0.09747 0.08991 0.0096 0.4659 1.0000
9.500 0.3752 0.09783 0.09026 0.0113 0.4529 1.0000
9.750 0.3740 0.10069 0.09314 0.0119 0.4526 1.0000
10.000 0.4080 0.09773 0.09013 0.0144 0.4225 1.0000
10.250 0.4578 0.09613 0.08852 0.0152 0.4150 1.0000
10.500 0.4344 0.09961 0.09202 0.0165 0.4050 1.0000
10.750 0.4698 0.09891 0.09134 0.0173 0.3981 1.0000
11.000 0.4614 0.10149 0.09393 0.0184 0.3881 1.0000
11.250 0.4867 0.10153 0.09399 0.0192 0.3812 1.0000
11.500 0.5439 0.09868 0.09115 0.0204 0.3779 1.0000
11.750 0.5116 0.10337 0.09587 0.0211 0.3640 1.0000
12.000 0.5613 0.10083 0.09335 0.0224 0.3609 1.0000
12.250 0.5359 0.10527 0.09782 0.0228 0.3471 1.0000
12.500 0.5840 0.10241 0.09498 0.0243 0.3440 1.0000
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