BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 106 AIRFOIL (boe106-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.84 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-boe106-il-1000000.txt Download as CSV file: xf-boe106-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 106 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9109 0.08032 0.07811 -0.0477 1.0000 0.0151
-15.750 -1.0538 0.04863 0.04591 -0.0716 1.0000 0.0144
-15.500 -1.0755 0.04074 0.03779 -0.0789 1.0000 0.0145
-15.250 -1.0843 0.03645 0.03334 -0.0819 1.0000 0.0146
-15.000 -1.0870 0.03361 0.03036 -0.0828 1.0000 0.0148
-14.750 -1.0870 0.03148 0.02809 -0.0825 1.0000 0.0150
-14.500 -1.0842 0.02984 0.02632 -0.0814 1.0000 0.0152
-14.250 -1.0791 0.02855 0.02492 -0.0797 1.0000 0.0153
-14.000 -1.0719 0.02755 0.02381 -0.0776 1.0000 0.0155
-13.750 -1.0733 0.02579 0.02191 -0.0748 1.0000 0.0158
-13.500 -1.0681 0.02472 0.02078 -0.0720 1.0000 0.0162
-13.250 -1.0599 0.02411 0.02013 -0.0692 1.0000 0.0164
-13.000 -1.0542 0.02366 0.01965 -0.0658 1.0000 0.0167
-12.750 -1.0261 0.02308 0.01902 -0.0666 0.9984 0.0171
-12.500 -0.9952 0.02249 0.01838 -0.0680 0.9964 0.0176
-12.250 -0.9638 0.02187 0.01768 -0.0695 0.9945 0.0181
-12.000 -0.9331 0.02127 0.01698 -0.0707 0.9924 0.0186
-11.750 -0.9027 0.02071 0.01633 -0.0718 0.9894 0.0189
-11.500 -0.8763 0.01926 0.01477 -0.0729 0.9862 0.0197
-11.250 -0.8443 0.01879 0.01429 -0.0743 0.9837 0.0201
-11.000 -0.8148 0.01840 0.01386 -0.0750 0.9792 0.0207
-10.750 -0.7865 0.01795 0.01335 -0.0754 0.9735 0.0212
-10.500 -0.7584 0.01749 0.01281 -0.0758 0.9679 0.0218
-10.250 -0.7335 0.01716 0.01240 -0.0754 0.9596 0.0223
-10.000 -0.7087 0.01679 0.01194 -0.0749 0.9517 0.0227
-9.750 -0.6891 0.01580 0.01086 -0.0737 0.9416 0.0236
-9.500 -0.6654 0.01547 0.01050 -0.0730 0.9316 0.0241
-9.250 -0.6412 0.01517 0.01014 -0.0724 0.9224 0.0247
-9.000 -0.6164 0.01485 0.00975 -0.0718 0.9130 0.0253
-8.750 -0.5914 0.01453 0.00935 -0.0713 0.9051 0.0260
-8.500 -0.5655 0.01430 0.00905 -0.0709 0.8966 0.0266
-8.250 -0.5391 0.01416 0.00882 -0.0706 0.8890 0.0270
-8.000 -0.5173 0.01312 0.00770 -0.0697 0.8804 0.0281
-7.750 -0.4918 0.01278 0.00732 -0.0694 0.8729 0.0287
-7.500 -0.4655 0.01252 0.00703 -0.0691 0.8649 0.0295
-7.250 -0.4392 0.01228 0.00672 -0.0687 0.8576 0.0303
-7.000 -0.4127 0.01201 0.00641 -0.0685 0.8498 0.0311
-6.500 -0.3592 0.01158 0.00585 -0.0680 0.8351 0.0321
-6.250 -0.3355 0.01088 0.00508 -0.0673 0.8276 0.0335
-6.000 -0.3089 0.01060 0.00478 -0.0670 0.8205 0.0344
-5.750 -0.2823 0.01037 0.00451 -0.0667 0.8131 0.0353
-5.500 -0.2554 0.01015 0.00425 -0.0665 0.8061 0.0362
-5.250 -0.2284 0.00996 0.00401 -0.0663 0.7986 0.0371
-5.000 -0.2011 0.00982 0.00382 -0.0661 0.7918 0.0379
-4.750 -0.1752 0.00944 0.00340 -0.0657 0.7842 0.0394
-4.500 -0.1487 0.00922 0.00313 -0.0654 0.7770 0.0409
-4.250 -0.1213 0.00904 0.00294 -0.0652 0.7694 0.0424
-3.750 -0.0669 0.00876 0.00258 -0.0648 0.7524 0.0457
-3.500 -0.0404 0.00856 0.00235 -0.0644 0.7429 0.0493
-3.250 -0.0132 0.00843 0.00219 -0.0642 0.7332 0.0525
-3.000 0.0138 0.00826 0.00201 -0.0640 0.7250 0.0591
-2.750 0.0404 0.00806 0.00187 -0.0637 0.7164 0.0758
-2.500 0.0669 0.00784 0.00178 -0.0634 0.7082 0.1121
-2.250 0.0939 0.00773 0.00170 -0.0632 0.6990 0.1327
-2.000 0.1212 0.00761 0.00162 -0.0631 0.6899 0.1507
-1.750 0.1479 0.00750 0.00154 -0.0628 0.6807 0.1740
-1.500 0.1738 0.00723 0.00147 -0.0625 0.6712 0.2368
-1.250 0.1992 0.00697 0.00142 -0.0621 0.6615 0.3137
-0.750 0.2490 0.00641 0.00134 -0.0611 0.6397 0.4875
-0.500 0.2717 0.00603 0.00133 -0.0601 0.6292 0.6146
-0.250 0.2956 0.00585 0.00135 -0.0593 0.6182 0.6975
0.000 0.3202 0.00572 0.00137 -0.0585 0.6073 0.7581
0.250 0.3441 0.00560 0.00141 -0.0574 0.5966 0.8182
0.500 0.3686 0.00556 0.00147 -0.0565 0.5853 0.8694
0.750 0.3954 0.00558 0.00154 -0.0560 0.5742 0.9029
1.000 0.4240 0.00565 0.00161 -0.0560 0.5638 0.9294
1.250 0.4540 0.00577 0.00169 -0.0563 0.5536 0.9465
1.500 0.4856 0.00586 0.00175 -0.0570 0.5440 0.9588
1.750 0.5168 0.00599 0.00184 -0.0577 0.5349 0.9703
2.000 0.5532 0.00612 0.00192 -0.0595 0.5252 0.9767
2.250 0.5893 0.00626 0.00201 -0.0613 0.5151 0.9832
2.500 0.6325 0.00641 0.00209 -0.0647 0.5018 0.9870
2.750 0.6717 0.00657 0.00217 -0.0672 0.4890 0.9915
3.000 0.7157 0.00670 0.00225 -0.0708 0.4760 0.9954
3.250 0.7577 0.00681 0.00230 -0.0740 0.4634 0.9984
3.500 0.7922 0.00692 0.00236 -0.0756 0.4525 1.0000
3.750 0.8157 0.00705 0.00244 -0.0748 0.4412 1.0000
4.000 0.8394 0.00716 0.00252 -0.0741 0.4301 1.0000
4.250 0.8626 0.00730 0.00261 -0.0732 0.4171 1.0000
4.500 0.8849 0.00748 0.00273 -0.0722 0.4007 1.0000
4.750 0.9072 0.00766 0.00285 -0.0712 0.3861 1.0000
5.000 0.9296 0.00784 0.00297 -0.0702 0.3745 1.0000
5.250 0.9515 0.00803 0.00312 -0.0691 0.3620 1.0000
5.500 0.9734 0.00822 0.00326 -0.0680 0.3502 1.0000
5.750 0.9959 0.00838 0.00341 -0.0670 0.3410 1.0000
6.000 1.0177 0.00859 0.00357 -0.0659 0.3313 1.0000
6.250 1.0398 0.00877 0.00373 -0.0648 0.3211 1.0000
6.500 1.0617 0.00898 0.00391 -0.0637 0.3102 1.0000
6.750 1.0831 0.00921 0.00410 -0.0626 0.2983 1.0000
7.000 1.1042 0.00946 0.00431 -0.0614 0.2852 1.0000
7.250 1.1250 0.00973 0.00452 -0.0602 0.2691 1.0000
7.500 1.1445 0.01011 0.00479 -0.0588 0.2449 1.0000
7.750 1.1592 0.01078 0.00522 -0.0566 0.2009 1.0000
8.000 1.1738 0.01150 0.00574 -0.0545 0.1672 1.0000
8.250 1.1926 0.01198 0.00614 -0.0531 0.1510 1.0000
8.500 1.2120 0.01243 0.00653 -0.0519 0.1380 1.0000
8.750 1.2312 0.01289 0.00693 -0.0506 0.1257 1.0000
9.000 1.2505 0.01333 0.00731 -0.0494 0.1149 1.0000
9.250 1.2701 0.01374 0.00770 -0.0482 0.1055 1.0000
9.500 1.2879 0.01419 0.00811 -0.0467 0.0964 1.0000
9.750 1.3038 0.01470 0.00857 -0.0450 0.0874 1.0000
10.000 1.3212 0.01515 0.00901 -0.0435 0.0815 1.0000
10.250 1.3371 0.01569 0.00953 -0.0419 0.0752 1.0000
10.500 1.3536 0.01620 0.01004 -0.0404 0.0704 1.0000
10.750 1.3684 0.01683 0.01066 -0.0388 0.0654 1.0000
11.000 1.3858 0.01733 0.01119 -0.0376 0.0630 1.0000
11.250 1.4011 0.01796 0.01183 -0.0362 0.0601 1.0000
11.500 1.4147 0.01871 0.01258 -0.0346 0.0567 1.0000
11.750 1.4308 0.01932 0.01325 -0.0335 0.0547 1.0000
12.000 1.4459 0.02001 0.01397 -0.0323 0.0524 1.0000
12.250 1.4586 0.02089 0.01485 -0.0309 0.0495 1.0000
12.500 1.4714 0.02178 0.01577 -0.0296 0.0469 1.0000
12.750 1.4858 0.02259 0.01662 -0.0286 0.0447 1.0000
13.000 1.4969 0.02366 0.01770 -0.0273 0.0417 1.0000
13.250 1.5081 0.02475 0.01882 -0.0262 0.0388 1.0000
13.500 1.5175 0.02600 0.02008 -0.0250 0.0349 1.0000
13.750 1.5250 0.02745 0.02153 -0.0238 0.0302 1.0000
14.000 1.5284 0.02927 0.02334 -0.0224 0.0248 1.0000
14.250 1.5304 0.03128 0.02536 -0.0211 0.0207 1.0000
14.500 1.5325 0.03336 0.02746 -0.0200 0.0182 1.0000
14.750 1.5335 0.03559 0.02974 -0.0190 0.0166 1.0000
15.000 1.5357 0.03779 0.03200 -0.0182 0.0155 1.0000
15.250 1.5380 0.04005 0.03433 -0.0176 0.0148 1.0000
15.500 1.5384 0.04256 0.03691 -0.0170 0.0141 1.0000
15.750 1.5366 0.04541 0.03983 -0.0166 0.0135 1.0000
16.000 1.5337 0.04848 0.04299 -0.0164 0.0130 1.0000
16.250 1.5345 0.05121 0.04581 -0.0163 0.0127 1.0000
16.500 1.5338 0.05418 0.04886 -0.0163 0.0124 1.0000
16.750 1.5321 0.05735 0.05213 -0.0165 0.0121 1.0000
17.000 1.5289 0.06076 0.05562 -0.0168 0.0118 1.0000
17.250 1.5240 0.06443 0.05938 -0.0172 0.0115 1.0000
17.500 1.5175 0.06839 0.06343 -0.0178 0.0113 1.0000
17.750 1.5087 0.07275 0.06789 -0.0186 0.0110 1.0000
18.000 1.4976 0.07748 0.07272 -0.0196 0.0108 1.0000
18.250 1.4838 0.08267 0.07802 -0.0208 0.0106 1.0000
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Polar data table (+)
Polar graphs
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