BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 200,000 Max Cl/Cd: 72.01 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-boe103-il-200000.txt Download as CSV file: xf-boe103-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 103 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3887 0.08786 0.08449 -0.0401 1.0000 0.0766
-8.500 -0.4271 0.08558 0.08234 -0.0387 1.0000 0.0777
-8.250 -0.4612 0.08403 0.08090 -0.0354 1.0000 0.0777
-8.000 -0.5030 0.07335 0.06998 -0.0487 0.9944 0.0795
-7.750 -0.4752 0.07128 0.06806 -0.0470 0.9929 0.0808
-7.500 -0.4499 0.06934 0.06614 -0.0475 0.9891 0.0828
-7.250 -0.4451 0.05952 0.05569 -0.0614 0.9774 0.0924
-7.000 -0.4158 0.05677 0.05313 -0.0621 0.9746 0.0941
-6.500 -0.3921 0.03275 0.02661 -0.0690 0.9597 0.0576
-6.250 -0.3641 0.02966 0.02318 -0.0700 0.9545 0.0574
-6.000 -0.3343 0.02696 0.02014 -0.0710 0.9490 0.0570
-5.750 -0.2975 0.02480 0.01765 -0.0730 0.9458 0.0569
-5.500 -0.2567 0.02346 0.01598 -0.0755 0.9436 0.0577
-5.250 -0.2314 0.02166 0.01406 -0.0752 0.9356 0.0588
-5.000 -0.1924 0.02033 0.01266 -0.0773 0.9323 0.0598
-4.750 -0.1505 0.01922 0.01150 -0.0800 0.9302 0.0612
-4.500 -0.1187 0.01842 0.01067 -0.0806 0.9238 0.0627
-4.250 -0.0831 0.01768 0.00989 -0.0820 0.9186 0.0653
-4.000 -0.0439 0.01695 0.00909 -0.0839 0.9153 0.0677
-3.750 -0.0148 0.01610 0.00833 -0.0841 0.9082 0.0707
-3.500 0.0182 0.01550 0.00774 -0.0848 0.9020 0.0750
-3.250 0.0547 0.01482 0.00707 -0.0863 0.8979 0.0826
-3.000 0.0794 0.01437 0.00673 -0.0854 0.8879 0.0999
-2.750 0.1119 0.01354 0.00626 -0.0862 0.8824 0.1837
-2.500 0.1363 0.01314 0.00606 -0.0855 0.8722 0.2356
-2.250 0.1654 0.01236 0.00575 -0.0858 0.8659 0.3531
-2.000 0.1842 0.01166 0.00574 -0.0839 0.8546 0.5346
-1.750 0.2075 0.01114 0.00566 -0.0822 0.8455 0.6694
-1.500 0.2310 0.01078 0.00557 -0.0803 0.8348 0.7625
-1.250 0.2549 0.01062 0.00555 -0.0783 0.8228 0.8363
-1.000 0.2882 0.01057 0.00552 -0.0780 0.8135 0.9041
-0.750 0.3324 0.01063 0.00550 -0.0803 0.8038 0.9492
-0.500 0.3853 0.01066 0.00542 -0.0849 0.7946 0.9735
-0.250 0.4446 0.01061 0.00521 -0.0911 0.7855 0.9909
0.000 0.4898 0.01056 0.00506 -0.0948 0.7740 1.0000
0.250 0.5126 0.01055 0.00495 -0.0939 0.7632 1.0000
0.500 0.5362 0.01056 0.00483 -0.0931 0.7526 1.0000
0.750 0.5582 0.01060 0.00481 -0.0919 0.7405 1.0000
1.000 0.5813 0.01065 0.00478 -0.0910 0.7293 1.0000
1.250 0.6058 0.01070 0.00471 -0.0902 0.7188 1.0000
1.500 0.6281 0.01078 0.00474 -0.0890 0.7065 1.0000
1.750 0.6510 0.01087 0.00475 -0.0879 0.6941 1.0000
2.000 0.6743 0.01095 0.00476 -0.0868 0.6814 1.0000
2.250 0.6975 0.01105 0.00476 -0.0857 0.6677 1.0000
2.500 0.7203 0.01115 0.00477 -0.0845 0.6528 1.0000
2.750 0.7427 0.01126 0.00480 -0.0832 0.6374 1.0000
3.000 0.7651 0.01140 0.00485 -0.0820 0.6217 1.0000
3.250 0.7874 0.01154 0.00492 -0.0807 0.6060 1.0000
3.500 0.8089 0.01169 0.00501 -0.0793 0.5883 1.0000
3.750 0.8301 0.01184 0.00511 -0.0778 0.5685 1.0000
4.000 0.8512 0.01202 0.00520 -0.0764 0.5474 1.0000
4.250 0.8723 0.01223 0.00530 -0.0749 0.5267 1.0000
4.500 0.8935 0.01244 0.00546 -0.0736 0.5054 1.0000
4.750 0.9145 0.01270 0.00563 -0.0722 0.4834 1.0000
5.000 0.9352 0.01300 0.00582 -0.0708 0.4619 1.0000
5.250 0.9560 0.01330 0.00607 -0.0694 0.4400 1.0000
5.500 0.9764 0.01365 0.00632 -0.0680 0.4190 1.0000
5.750 0.9966 0.01404 0.00660 -0.0667 0.3996 1.0000
6.000 1.0168 0.01445 0.00693 -0.0653 0.3814 1.0000
6.250 1.0371 0.01487 0.00728 -0.0640 0.3641 1.0000
6.500 1.0570 0.01530 0.00765 -0.0627 0.3471 1.0000
6.750 1.0765 0.01575 0.00805 -0.0613 0.3299 1.0000
7.000 1.0955 0.01622 0.00848 -0.0599 0.3122 1.0000
7.250 1.1136 0.01670 0.00891 -0.0583 0.2933 1.0000
7.500 1.1302 0.01724 0.00938 -0.0565 0.2727 1.0000
7.750 1.1461 0.01780 0.00987 -0.0547 0.2478 1.0000
8.000 1.1589 0.01852 0.01047 -0.0524 0.2211 1.0000
8.250 1.1692 0.01932 0.01112 -0.0497 0.1984 1.0000
8.500 1.1797 0.02020 0.01188 -0.0471 0.1826 1.0000
8.750 1.1924 0.02102 0.01265 -0.0450 0.1713 1.0000
9.000 1.2047 0.02191 0.01350 -0.0429 0.1635 1.0000
9.250 1.2189 0.02271 0.01430 -0.0411 0.1570 1.0000
9.500 1.2307 0.02373 0.01524 -0.0391 0.1520 1.0000
9.750 1.2471 0.02447 0.01607 -0.0377 0.1478 1.0000
10.000 1.2620 0.02528 0.01693 -0.0362 0.1436 1.0000
10.250 1.2750 0.02631 0.01789 -0.0346 0.1394 1.0000
10.500 1.2900 0.02717 0.01883 -0.0333 0.1356 1.0000
10.750 1.3045 0.02801 0.01976 -0.0319 0.1318 1.0000
11.000 1.3173 0.02895 0.02073 -0.0305 0.1279 1.0000
11.250 1.3309 0.03012 0.02183 -0.0292 0.1241 1.0000
11.500 1.3437 0.03103 0.02290 -0.0279 0.1211 1.0000
11.750 1.3562 0.03203 0.02400 -0.0266 0.1179 1.0000
12.000 1.3676 0.03313 0.02514 -0.0254 0.1148 1.0000
12.250 1.3812 0.03439 0.02634 -0.0242 0.1115 1.0000
12.500 1.3909 0.03557 0.02770 -0.0230 0.1090 1.0000
12.750 1.3997 0.03683 0.02910 -0.0218 0.1059 1.0000
13.000 1.4083 0.03816 0.03051 -0.0207 0.1030 1.0000
13.250 1.4171 0.03958 0.03194 -0.0196 0.1003 1.0000
13.500 1.4278 0.04104 0.03343 -0.0186 0.0977 1.0000
13.750 1.4334 0.04266 0.03526 -0.0176 0.0955 1.0000
14.000 1.4391 0.04435 0.03710 -0.0168 0.0930 1.0000
14.250 1.4444 0.04610 0.03894 -0.0160 0.0906 1.0000
14.500 1.4492 0.04795 0.04084 -0.0154 0.0883 1.0000
14.750 1.4567 0.04970 0.04259 -0.0145 0.0859 1.0000
15.000 1.4581 0.05198 0.04509 -0.0142 0.0842 1.0000
15.250 1.4601 0.05428 0.04758 -0.0139 0.0823 1.0000
15.500 1.4620 0.05665 0.05010 -0.0137 0.0803 1.0000
15.750 1.4629 0.05921 0.05276 -0.0139 0.0781 1.0000
16.000 1.4639 0.06182 0.05543 -0.0140 0.0763 1.0000
16.250 1.4649 0.06448 0.05814 -0.0141 0.0744 1.0000
16.500 1.4626 0.06781 0.06172 -0.0148 0.0726 1.0000
16.750 1.4606 0.07119 0.06529 -0.0157 0.0705 1.0000
17.000 1.4585 0.07467 0.06892 -0.0167 0.0684 1.0000
17.250 1.4555 0.07836 0.07273 -0.0179 0.0665 1.0000
17.500 1.4515 0.08220 0.07662 -0.0191 0.0648 1.0000
17.750 1.4470 0.08631 0.08095 -0.0205 0.0629 1.0000
18.000 1.4419 0.09060 0.08545 -0.0221 0.0606 1.0000
18.250 1.4351 0.09530 0.09030 -0.0241 0.0581 1.0000
18.500 1.4263 0.10038 0.09548 -0.0264 0.0561 1.0000
18.750 1.4177 0.10544 0.10071 -0.0285 0.0537 1.0000
19.000 1.4070 0.11099 0.10642 -0.0311 0.0511 1.0000
19.250 1.3940 0.11703 0.11256 -0.0340 0.0489 1.0000
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