BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 500,000 Max Cl/Cd: 94.57 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-boe103-il-500000.txt Download as CSV file: xf-boe103-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2866 0.11058 0.10831 -0.0414 1.0000 0.0303
-11.500 -0.3957 0.10895 0.10649 -0.0416 1.0000 0.0298
-11.250 -0.3886 0.10705 0.10460 -0.0411 1.0000 0.0301
-11.000 -0.3829 0.10487 0.10244 -0.0410 1.0000 0.0305
-10.750 -0.3793 0.10230 0.09988 -0.0412 1.0000 0.0310
-10.500 -0.3779 0.09934 0.09694 -0.0416 1.0000 0.0316
-10.250 -0.3796 0.09586 0.09350 -0.0424 1.0000 0.0324
-9.250 -0.5685 0.03950 0.03586 -0.0786 0.9838 0.0296
-9.000 -0.5570 0.03471 0.03065 -0.0798 0.9773 0.0297
-8.750 -0.5373 0.03022 0.02579 -0.0815 0.9737 0.0300
-8.500 -0.5094 0.02737 0.02270 -0.0834 0.9717 0.0304
-8.250 -0.4825 0.02625 0.02161 -0.0840 0.9669 0.0311
-8.000 -0.4543 0.02440 0.01955 -0.0850 0.9631 0.0316
-7.750 -0.4225 0.02288 0.01783 -0.0865 0.9606 0.0324
-7.500 -0.3903 0.02137 0.01608 -0.0879 0.9584 0.0333
-7.250 -0.3655 0.02006 0.01455 -0.0875 0.9518 0.0337
-7.000 -0.3353 0.01887 0.01316 -0.0881 0.9474 0.0342
-6.750 -0.3028 0.01801 0.01212 -0.0891 0.9440 0.0347
-6.500 -0.2776 0.01688 0.01083 -0.0887 0.9364 0.0354
-6.250 -0.2484 0.01548 0.00936 -0.0891 0.9311 0.0361
-6.000 -0.2204 0.01464 0.00849 -0.0891 0.9244 0.0366
-5.750 -0.1926 0.01396 0.00777 -0.0891 0.9171 0.0373
-5.500 -0.1645 0.01338 0.00713 -0.0890 0.9099 0.0379
-5.250 -0.1377 0.01289 0.00660 -0.0887 0.9015 0.0388
-5.000 -0.1104 0.01246 0.00611 -0.0884 0.8938 0.0397
-4.750 -0.0841 0.01204 0.00564 -0.0880 0.8851 0.0404
-4.500 -0.0575 0.01167 0.00521 -0.0875 0.8766 0.0409
-4.250 -0.0309 0.01136 0.00483 -0.0871 0.8679 0.0414
-4.000 -0.0057 0.01087 0.00432 -0.0865 0.8589 0.0424
-3.750 0.0207 0.01051 0.00391 -0.0861 0.8503 0.0439
-3.500 0.0467 0.01026 0.00364 -0.0856 0.8406 0.0456
-3.250 0.0739 0.01006 0.00337 -0.0852 0.8315 0.0474
-3.000 0.1002 0.00988 0.00314 -0.0847 0.8201 0.0490
-2.750 0.1264 0.00966 0.00290 -0.0841 0.8085 0.0534
-2.500 0.1528 0.00944 0.00270 -0.0837 0.7974 0.0670
-2.250 0.1780 0.00907 0.00257 -0.0831 0.7853 0.1344
-2.000 0.2038 0.00885 0.00247 -0.0826 0.7726 0.1767
-1.750 0.2297 0.00863 0.00236 -0.0822 0.7608 0.2215
-1.500 0.2543 0.00822 0.00226 -0.0817 0.7503 0.3251
-1.250 0.2775 0.00771 0.00222 -0.0809 0.7388 0.4784
-1.000 0.3015 0.00741 0.00221 -0.0801 0.7277 0.5767
-0.750 0.3258 0.00721 0.00222 -0.0791 0.7174 0.6610
-0.500 0.3498 0.00704 0.00223 -0.0781 0.7063 0.7328
-0.250 0.3729 0.00687 0.00229 -0.0767 0.6954 0.8072
0.000 0.3968 0.00682 0.00235 -0.0753 0.6851 0.8700
0.250 0.4238 0.00686 0.00244 -0.0746 0.6745 0.9231
0.500 0.4603 0.00698 0.00252 -0.0759 0.6624 0.9597
0.750 0.5004 0.00711 0.00257 -0.0783 0.6491 0.9773
1.000 0.5437 0.00724 0.00259 -0.0815 0.6365 0.9861
1.250 0.5869 0.00735 0.00262 -0.0848 0.6235 0.9940
1.500 0.6327 0.00745 0.00262 -0.0887 0.6077 1.0000
1.750 0.6553 0.00753 0.00264 -0.0877 0.5937 1.0000
2.000 0.6779 0.00763 0.00267 -0.0866 0.5798 1.0000
2.250 0.7004 0.00774 0.00271 -0.0855 0.5655 1.0000
2.500 0.7227 0.00786 0.00276 -0.0844 0.5507 1.0000
2.750 0.7447 0.00799 0.00282 -0.0831 0.5336 1.0000
3.000 0.7662 0.00816 0.00289 -0.0818 0.5142 1.0000
3.500 0.8086 0.00855 0.00308 -0.0791 0.4705 1.0000
3.750 0.8294 0.00878 0.00321 -0.0777 0.4474 1.0000
4.000 0.8504 0.00904 0.00335 -0.0763 0.4229 1.0000
4.250 0.8708 0.00935 0.00353 -0.0749 0.3978 1.0000
4.500 0.8919 0.00966 0.00372 -0.0736 0.3737 1.0000
4.750 0.9130 0.01000 0.00394 -0.0724 0.3523 1.0000
5.000 0.9347 0.01033 0.00416 -0.0713 0.3343 1.0000
5.250 0.9570 0.01063 0.00439 -0.0703 0.3186 1.0000
5.500 0.9798 0.01092 0.00462 -0.0694 0.3042 1.0000
5.750 1.0028 0.01120 0.00485 -0.0686 0.2899 1.0000
6.000 1.0257 0.01150 0.00509 -0.0677 0.2751 1.0000
6.250 1.0482 0.01181 0.00534 -0.0669 0.2592 1.0000
6.500 1.0698 0.01218 0.00562 -0.0659 0.2408 1.0000
6.750 1.0910 0.01259 0.00593 -0.0648 0.2179 1.0000
7.000 1.1101 0.01312 0.00631 -0.0635 0.1900 1.0000
7.250 1.1279 0.01374 0.00677 -0.0619 0.1633 1.0000
7.500 1.1459 0.01434 0.00724 -0.0604 0.1429 1.0000
7.750 1.1646 0.01487 0.00770 -0.0590 0.1305 1.0000
8.000 1.1834 0.01537 0.00816 -0.0576 0.1228 1.0000
8.250 1.2020 0.01580 0.00859 -0.0562 0.1176 1.0000
8.500 1.2187 0.01633 0.00908 -0.0544 0.1127 1.0000
8.750 1.2371 0.01676 0.00955 -0.0530 0.1094 1.0000
9.000 1.2557 0.01719 0.01000 -0.0517 0.1063 1.0000
9.250 1.2731 0.01769 0.01051 -0.0502 0.1034 1.0000
9.500 1.2888 0.01829 0.01111 -0.0485 0.1004 1.0000
9.750 1.3046 0.01889 0.01174 -0.0469 0.0977 1.0000
10.000 1.3233 0.01933 0.01224 -0.0457 0.0957 1.0000
10.250 1.3406 0.01985 0.01281 -0.0444 0.0936 1.0000
10.500 1.3567 0.02046 0.01345 -0.0430 0.0914 1.0000
10.750 1.3709 0.02119 0.01420 -0.0415 0.0891 1.0000
11.000 1.3820 0.02213 0.01517 -0.0396 0.0864 1.0000
11.250 1.4003 0.02264 0.01575 -0.0387 0.0846 1.0000
11.500 1.4175 0.02322 0.01640 -0.0377 0.0824 1.0000
11.750 1.4328 0.02395 0.01717 -0.0366 0.0801 1.0000
12.000 1.4461 0.02482 0.01808 -0.0353 0.0777 1.0000
12.250 1.4558 0.02598 0.01925 -0.0337 0.0750 1.0000
12.500 1.4731 0.02662 0.01997 -0.0330 0.0730 1.0000
12.750 1.4890 0.02736 0.02079 -0.0322 0.0701 1.0000
13.000 1.5020 0.02835 0.02178 -0.0312 0.0666 1.0000
13.250 1.5140 0.02943 0.02290 -0.0301 0.0635 1.0000
13.500 1.5275 0.03041 0.02394 -0.0293 0.0592 1.0000
13.750 1.5377 0.03169 0.02521 -0.0283 0.0539 1.0000
14.000 1.5440 0.03333 0.02680 -0.0272 0.0457 1.0000
14.250 1.5469 0.03531 0.02876 -0.0260 0.0403 1.0000
14.500 1.5494 0.03740 0.03088 -0.0250 0.0365 1.0000
14.750 1.5510 0.03963 0.03316 -0.0241 0.0333 1.0000
15.000 1.5514 0.04206 0.03564 -0.0233 0.0303 1.0000
15.250 1.5531 0.04447 0.03812 -0.0227 0.0272 1.0000
15.750 1.5415 0.05112 0.04482 -0.0219 0.0161 1.0000
16.000 1.5341 0.05485 0.04862 -0.0219 0.0150 1.0000
16.250 1.5288 0.05845 0.05232 -0.0220 0.0142 1.0000
16.500 1.5235 0.06215 0.05614 -0.0223 0.0139 1.0000
16.750 1.5167 0.06616 0.06029 -0.0229 0.0136 1.0000
17.000 1.5085 0.07047 0.06473 -0.0237 0.0133 1.0000
17.250 1.4983 0.07514 0.06955 -0.0247 0.0131 1.0000
17.500 1.4864 0.08020 0.07475 -0.0260 0.0129 1.0000
17.750 1.4729 0.08564 0.08033 -0.0276 0.0128 1.0000
18.000 1.4582 0.09137 0.08620 -0.0294 0.0127 1.0000
18.250 1.4426 0.09738 0.09236 -0.0315 0.0126 1.0000
18.500 1.4258 0.10373 0.09885 -0.0338 0.0125 1.0000
18.750 1.4083 0.11032 0.10559 -0.0365 0.0124 1.0000
19.000 1.3904 0.11707 0.11247 -0.0393 0.0123 1.0000
19.250 1.3729 0.12388 0.11941 -0.0423 0.0123 1.0000
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