B-29 ROOT AIRFOIL (b29root-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: B-29 ROOT AIRFOIL (b29root-il) Reynolds number: 100,000 Max Cl/Cd: 34.58 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b29root-il-100000-n5.txt Download as CSV file: xf-b29root-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.7437 0.08837 0.08133 -0.0718 1.0000 0.0814
-16.750 -0.7818 0.08021 0.07292 -0.0757 1.0000 0.0820
-16.500 -0.8048 0.07454 0.06705 -0.0779 1.0000 0.0828
-16.250 -0.8230 0.06978 0.06209 -0.0794 1.0000 0.0836
-16.000 -0.8379 0.06563 0.05775 -0.0804 1.0000 0.0845
-15.750 -0.8524 0.06180 0.05370 -0.0810 1.0000 0.0855
-15.500 -0.8647 0.05839 0.05005 -0.0811 1.0000 0.0865
-15.250 -0.8609 0.05638 0.04799 -0.0809 1.0000 0.0875
-15.000 -0.8507 0.05494 0.04658 -0.0805 1.0000 0.0885
-14.750 -0.8446 0.05326 0.04487 -0.0801 1.0000 0.0897
-14.500 -0.8404 0.05150 0.04305 -0.0795 1.0000 0.0909
-14.250 -0.8367 0.04973 0.04120 -0.0789 1.0000 0.0922
-14.000 -0.8342 0.04796 0.03931 -0.0780 1.0000 0.0937
-13.750 -0.8315 0.04625 0.03746 -0.0770 1.0000 0.0952
-13.500 -0.8227 0.04496 0.03615 -0.0761 1.0000 0.0966
-13.250 -0.8116 0.04392 0.03518 -0.0751 1.0000 0.0981
-13.000 -0.8034 0.04281 0.03410 -0.0739 1.0000 0.0996
-12.750 -0.7965 0.04175 0.03303 -0.0725 1.0000 0.1013
-12.500 -0.7847 0.04037 0.03162 -0.0720 0.9896 0.1034
-12.000 -0.7203 0.03768 0.02884 -0.0781 0.9442 0.1091
-11.750 -0.6866 0.03639 0.02746 -0.0814 0.9269 0.1127
-11.500 -0.6527 0.03515 0.02604 -0.0845 0.9101 0.1167
-11.250 -0.6223 0.03401 0.02492 -0.0870 0.8935 0.1203
-11.000 -0.5982 0.03300 0.02381 -0.0882 0.8769 0.1246
-10.750 -0.5773 0.03211 0.02279 -0.0885 0.8616 0.1289
-10.500 -0.5609 0.03120 0.02186 -0.0882 0.8482 0.1328
-10.250 -0.5458 0.03039 0.02096 -0.0874 0.8358 0.1375
-10.000 -0.5330 0.02961 0.02012 -0.0862 0.8243 0.1426
-9.750 -0.5219 0.02878 0.01926 -0.0848 0.8141 0.1479
-9.500 -0.5099 0.02808 0.01849 -0.0832 0.8041 0.1543
-9.250 -0.5015 0.02727 0.01769 -0.0812 0.7949 0.1604
-9.000 -0.4903 0.02659 0.01695 -0.0794 0.7866 0.1686
-8.750 -0.4830 0.02583 0.01625 -0.0771 0.7777 0.1768
-8.500 -0.4732 0.02515 0.01554 -0.0749 0.7706 0.1872
-8.250 -0.4659 0.02452 0.01494 -0.0723 0.7623 0.1996
-8.000 -0.4597 0.02387 0.01436 -0.0694 0.7548 0.2149
-7.750 -0.4525 0.02326 0.01379 -0.0665 0.7488 0.2342
-7.500 -0.4476 0.02273 0.01339 -0.0631 0.7410 0.2554
-7.250 -0.4410 0.02227 0.01300 -0.0598 0.7339 0.2794
-7.000 -0.4322 0.02188 0.01261 -0.0567 0.7283 0.3037
-6.750 -0.4247 0.02159 0.01238 -0.0534 0.7216 0.3252
-6.500 -0.4164 0.02138 0.01219 -0.0501 0.7149 0.3451
-6.250 -0.4064 0.02119 0.01198 -0.0468 0.7093 0.3639
-6.000 -0.3960 0.02106 0.01182 -0.0437 0.7040 0.3816
-5.750 -0.3859 0.02098 0.01180 -0.0405 0.6972 0.3976
-5.500 -0.3720 0.02086 0.01169 -0.0379 0.6914 0.4134
-5.250 -0.3559 0.02073 0.01150 -0.0357 0.6866 0.4288
-5.000 -0.3409 0.02066 0.01140 -0.0333 0.6811 0.4437
-4.750 -0.3249 0.02060 0.01137 -0.0311 0.6748 0.4575
-4.500 -0.3062 0.02050 0.01126 -0.0293 0.6694 0.4712
-4.250 -0.2870 0.02039 0.01108 -0.0276 0.6651 0.4855
-4.000 -0.2686 0.02035 0.01106 -0.0258 0.6599 0.4993
-3.750 -0.2508 0.02033 0.01110 -0.0239 0.6538 0.5141
-3.500 -0.2326 0.02027 0.01106 -0.0220 0.6487 0.5320
-3.250 -0.2123 0.02020 0.01098 -0.0203 0.6445 0.5506
-3.000 -0.1950 0.02020 0.01099 -0.0183 0.6397 0.5674
-2.750 -0.1731 0.02023 0.01109 -0.0171 0.6339 0.5801
-2.500 -0.1497 0.02018 0.01103 -0.0162 0.6290 0.5921
-2.250 -0.1253 0.02009 0.01088 -0.0154 0.6248 0.6050
-2.000 -0.0985 0.02008 0.01088 -0.0151 0.6204 0.6166
-1.750 -0.0811 0.02015 0.01097 -0.0133 0.6145 0.6298
-1.500 -0.0543 0.02018 0.01104 -0.0130 0.6097 0.6422
-1.250 -0.0272 0.02016 0.01099 -0.0127 0.6058 0.6553
-1.000 -0.0010 0.02010 0.01086 -0.0122 0.6024 0.6695
-0.750 0.0231 0.02031 0.01118 -0.0116 0.5963 0.6817
-0.500 0.0463 0.02040 0.01129 -0.0107 0.5912 0.6955
-0.250 0.0736 0.02045 0.01131 -0.0105 0.5871 0.7095
0.000 0.1099 0.02051 0.01134 -0.0119 0.5838 0.7217
0.250 0.1319 0.02069 0.01155 -0.0108 0.5791 0.7359
0.500 0.1593 0.02096 0.01188 -0.0108 0.5737 0.7483
0.750 0.1911 0.02112 0.01204 -0.0114 0.5692 0.7606
1.000 0.2174 0.02117 0.01204 -0.0110 0.5656 0.7746
1.250 0.2618 0.02138 0.01221 -0.0139 0.5623 0.7833
1.500 0.2768 0.02177 0.01269 -0.0118 0.5569 0.7972
1.750 0.3143 0.02212 0.01307 -0.0136 0.5520 0.8054
2.000 0.3397 0.02227 0.01319 -0.0131 0.5481 0.8180
2.250 0.3864 0.02245 0.01330 -0.0164 0.5448 0.8243
2.500 0.4032 0.02277 0.01366 -0.0145 0.5406 0.8374
2.750 0.4395 0.02331 0.01427 -0.0164 0.5354 0.8434
3.000 0.4589 0.02356 0.01452 -0.0149 0.5313 0.8557
3.250 0.5020 0.02378 0.01470 -0.0177 0.5276 0.8607
3.500 0.5436 0.02393 0.01478 -0.0201 0.5246 0.8664
3.750 0.5556 0.02453 0.01549 -0.0177 0.5196 0.8783
4.000 0.5872 0.02505 0.01607 -0.0188 0.5148 0.8842
4.250 0.6067 0.02528 0.01629 -0.0174 0.5110 0.8957
4.500 0.6505 0.02543 0.01641 -0.0204 0.5076 0.8996
4.750 0.6868 0.02565 0.01659 -0.0221 0.5045 0.9058
5.000 0.6977 0.02643 0.01752 -0.0199 0.4991 0.9168
5.250 0.7271 0.02689 0.01804 -0.0208 0.4945 0.9239
5.500 0.7529 0.02709 0.01822 -0.0206 0.4909 0.9328
5.750 0.7959 0.02716 0.01826 -0.0236 0.4880 0.9369
6.000 0.8188 0.02766 0.01882 -0.0234 0.4841 0.9459
6.250 0.8387 0.02849 0.01980 -0.0233 0.4787 0.9538
6.500 0.8642 0.02889 0.02025 -0.0236 0.4744 0.9621
6.750 0.9021 0.02898 0.02033 -0.0258 0.4712 0.9669
7.000 0.9445 0.02894 0.02027 -0.0286 0.4685 0.9709
7.250 0.9563 0.02999 0.02149 -0.0276 0.4632 0.9803
7.500 0.9788 0.03070 0.02232 -0.0282 0.4579 0.9874
7.750 1.0114 0.03092 0.02258 -0.0298 0.4542 0.9926
8.000 1.0532 0.03082 0.02248 -0.0326 0.4513 0.9962
8.250 1.0791 0.03121 0.02293 -0.0333 0.4476 1.0000
8.500 0.9937 0.03331 0.02516 -0.0171 0.4415 1.0000
8.750 0.9678 0.03445 0.02632 -0.0101 0.4369 1.0000
9.000 0.9869 0.03438 0.02625 -0.0086 0.4340 1.0000
9.250 1.0396 0.03331 0.02512 -0.0112 0.4314 1.0000
9.500 0.8632 0.04175 0.03370 0.0089 0.4175 1.0000
9.750 0.9059 0.04006 0.03199 0.0089 0.4156 1.0000
10.000 0.9701 0.03736 0.02924 0.0069 0.4136 1.0000
10.250 0.7771 0.05214 0.04413 0.0198 0.3890 1.0000
10.500 0.8902 0.04415 0.03611 0.0177 0.3966 1.0000
10.750 0.9395 0.04195 0.03390 0.0174 0.3952 1.0000
11.250 0.8687 0.05012 0.04215 0.0246 0.3766 1.0000
11.750 0.8346 0.05659 0.04868 0.0285 0.3587 1.0000
12.250 0.7718 0.06715 0.05934 0.0311 0.3328 1.0000
12.500 0.8009 0.06570 0.05790 0.0322 0.3298 1.0000
12.750 0.8384 0.06336 0.05556 0.0333 0.3276 1.0000
13.250 0.8436 0.06673 0.05899 0.0351 0.3111 1.0000
13.750 0.8517 0.07003 0.06235 0.0365 0.2946 1.0000
14.250 0.8629 0.07317 0.06555 0.0377 0.2780 1.0000
14.750 0.8617 0.07810 0.07054 0.0383 0.2582 1.0000
15.000 0.8661 0.07999 0.07245 0.0386 0.2483 1.0000
15.250 0.8661 0.08251 0.07499 0.0388 0.2378 1.0000
15.500 0.8903 0.08177 0.07420 0.0396 0.2303 1.0000
15.750 0.8858 0.08496 0.07741 0.0395 0.2187 1.0000
16.000 0.8919 0.08672 0.07915 0.0397 0.2086 1.0000
16.250 0.9064 0.08728 0.07962 0.0402 0.1994 1.0000
16.500 0.9077 0.08975 0.08207 0.0401 0.1891 1.0000
16.750 0.9121 0.09178 0.08406 0.0402 0.1799 1.0000
17.250 0.9199 0.09603 0.08821 0.0401 0.1632 1.0000
17.500 0.9262 0.09781 0.08990 0.0402 0.1561 1.0000
17.750 0.9271 0.10049 0.09261 0.0398 0.1490 1.0000
18.000 0.9325 0.10247 0.09453 0.0397 0.1428 1.0000
|
Polar data table (+)
Polar graphs
<< Back to B-29 ROOT AIRFOIL (b29root-il)