BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 200,000 Max Cl/Cd: 66.6 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-boe103-il-200000-n5.txt Download as CSV file: xf-boe103-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5578 0.05790 0.05422 -0.0646 1.0000 0.0262
-9.750 -0.5955 0.05033 0.04631 -0.0680 0.9944 0.0262
-9.500 -0.6053 0.04111 0.03616 -0.0740 0.9838 0.0267
-9.250 -0.5875 0.03834 0.03324 -0.0753 0.9773 0.0272
-9.000 -0.5608 0.03661 0.03140 -0.0772 0.9736 0.0280
-8.750 -0.5398 0.03488 0.02951 -0.0778 0.9667 0.0288
-8.250 -0.4953 0.03002 0.02389 -0.0794 0.9552 0.0306
-8.000 -0.4691 0.02789 0.02132 -0.0803 0.9504 0.0314
-7.750 -0.4404 0.02647 0.01944 -0.0812 0.9463 0.0323
-7.500 -0.4167 0.02468 0.01755 -0.0812 0.9395 0.0332
-7.250 -0.3864 0.02341 0.01617 -0.0822 0.9354 0.0339
-7.000 -0.3568 0.02229 0.01490 -0.0829 0.9307 0.0346
-6.750 -0.3296 0.02133 0.01381 -0.0830 0.9240 0.0354
-6.500 -0.2979 0.02042 0.01276 -0.0839 0.9196 0.0366
-6.250 -0.2682 0.01960 0.01180 -0.0844 0.9139 0.0376
-6.000 -0.2396 0.01881 0.01089 -0.0845 0.9071 0.0382
-5.750 -0.2072 0.01805 0.01002 -0.0854 0.9024 0.0388
-5.500 -0.1803 0.01736 0.00927 -0.0852 0.8947 0.0393
-5.250 -0.1514 0.01657 0.00847 -0.0855 0.8881 0.0403
-5.000 -0.1231 0.01600 0.00789 -0.0857 0.8811 0.0416
-4.750 -0.0955 0.01553 0.00739 -0.0856 0.8731 0.0429
-4.500 -0.0667 0.01507 0.00687 -0.0857 0.8660 0.0440
-4.250 -0.0401 0.01469 0.00643 -0.0854 0.8573 0.0451
-4.000 -0.0115 0.01434 0.00600 -0.0854 0.8498 0.0462
-3.750 0.0149 0.01401 0.00563 -0.0850 0.8407 0.0477
-3.500 0.0428 0.01369 0.00527 -0.0849 0.8328 0.0500
-3.250 0.0695 0.01343 0.00498 -0.0845 0.8236 0.0537
-3.000 0.0966 0.01314 0.00472 -0.0843 0.8151 0.0618
-2.750 0.1231 0.01281 0.00450 -0.0839 0.8060 0.0876
-2.500 0.1495 0.01254 0.00435 -0.0836 0.7969 0.1248
-2.250 0.1767 0.01233 0.00419 -0.0834 0.7880 0.1563
-2.000 0.2029 0.01214 0.00406 -0.0830 0.7773 0.1853
-1.750 0.2293 0.01193 0.00390 -0.0826 0.7660 0.2181
-1.500 0.2541 0.01151 0.00375 -0.0821 0.7535 0.3004
-1.250 0.2763 0.01095 0.00369 -0.0810 0.7394 0.4532
-1.000 0.2995 0.01063 0.00366 -0.0799 0.7261 0.5514
-0.750 0.3224 0.01035 0.00368 -0.0786 0.7145 0.6501
-0.500 0.3454 0.01013 0.00371 -0.0770 0.7044 0.7413
-0.250 0.3699 0.01000 0.00381 -0.0755 0.6937 0.8314
0.000 0.4040 0.01002 0.00388 -0.0761 0.6831 0.9012
0.250 0.4419 0.01010 0.00387 -0.0778 0.6725 0.9394
0.500 0.4818 0.01019 0.00388 -0.0801 0.6608 0.9647
0.750 0.5231 0.01028 0.00387 -0.0829 0.6495 0.9844
1.000 0.5721 0.01036 0.00384 -0.0874 0.6375 0.9997
1.250 0.5953 0.01046 0.00385 -0.0865 0.6262 1.0000
1.500 0.6182 0.01056 0.00388 -0.0855 0.6150 1.0000
1.750 0.6410 0.01069 0.00392 -0.0844 0.6031 1.0000
2.000 0.6632 0.01083 0.00396 -0.0833 0.5886 1.0000
2.250 0.6852 0.01098 0.00402 -0.0820 0.5724 1.0000
2.500 0.7069 0.01114 0.00409 -0.0807 0.5551 1.0000
2.750 0.7286 0.01131 0.00417 -0.0795 0.5368 1.0000
3.000 0.7505 0.01150 0.00427 -0.0782 0.5187 1.0000
3.250 0.7720 0.01171 0.00438 -0.0770 0.4983 1.0000
3.500 0.7931 0.01195 0.00450 -0.0756 0.4759 1.0000
3.750 0.8139 0.01222 0.00465 -0.0742 0.4505 1.0000
4.000 0.8341 0.01254 0.00483 -0.0728 0.4239 1.0000
4.250 0.8538 0.01290 0.00503 -0.0713 0.3973 1.0000
4.500 0.8744 0.01325 0.00527 -0.0700 0.3754 1.0000
4.750 0.8956 0.01360 0.00553 -0.0688 0.3583 1.0000
5.000 0.9168 0.01395 0.00580 -0.0677 0.3429 1.0000
5.250 0.9379 0.01432 0.00610 -0.0665 0.3280 1.0000
5.500 0.9589 0.01470 0.00642 -0.0654 0.3130 1.0000
5.750 0.9796 0.01509 0.00675 -0.0642 0.2978 1.0000
6.000 1.0003 0.01549 0.00708 -0.0631 0.2820 1.0000
6.250 1.0207 0.01590 0.00744 -0.0619 0.2655 1.0000
6.500 1.0408 0.01632 0.00781 -0.0607 0.2482 1.0000
6.750 1.0602 0.01678 0.00820 -0.0594 0.2300 1.0000
7.000 1.0787 0.01729 0.00863 -0.0580 0.2109 1.0000
7.250 1.0961 0.01785 0.00911 -0.0565 0.1918 1.0000
7.500 1.1126 0.01844 0.00962 -0.0548 0.1737 1.0000
7.750 1.1278 0.01905 0.01016 -0.0530 0.1587 1.0000
8.000 1.1429 0.01969 0.01075 -0.0511 0.1467 1.0000
8.250 1.1582 0.02034 0.01137 -0.0493 0.1371 1.0000
8.500 1.1739 0.02096 0.01201 -0.0477 0.1304 1.0000
8.750 1.1892 0.02162 0.01268 -0.0460 0.1250 1.0000
9.000 1.2035 0.02234 0.01341 -0.0443 0.1209 1.0000
9.250 1.2191 0.02300 0.01414 -0.0428 0.1178 1.0000
9.500 1.2339 0.02372 0.01491 -0.0413 0.1148 1.0000
9.750 1.2474 0.02454 0.01576 -0.0397 0.1118 1.0000
10.000 1.2591 0.02548 0.01672 -0.0380 0.1088 1.0000
10.250 1.2732 0.02630 0.01762 -0.0366 0.1058 1.0000
10.500 1.2869 0.02716 0.01856 -0.0353 0.1026 1.0000
10.750 1.2988 0.02816 0.01960 -0.0339 0.0992 1.0000
11.000 1.3081 0.02937 0.02082 -0.0323 0.0960 1.0000
11.250 1.3208 0.03038 0.02191 -0.0312 0.0932 1.0000
11.500 1.3335 0.03140 0.02304 -0.0301 0.0902 1.0000
11.750 1.3443 0.03259 0.02429 -0.0289 0.0873 1.0000
12.000 1.3533 0.03395 0.02570 -0.0278 0.0849 1.0000
12.250 1.3599 0.03554 0.02734 -0.0266 0.0827 1.0000
12.500 1.3716 0.03675 0.02866 -0.0257 0.0806 1.0000
12.750 1.3825 0.03806 0.03011 -0.0249 0.0782 1.0000
13.000 1.3917 0.03953 0.03169 -0.0241 0.0757 1.0000
13.250 1.3989 0.04122 0.03344 -0.0234 0.0731 1.0000
13.500 1.4046 0.04310 0.03538 -0.0227 0.0703 1.0000
13.750 1.4149 0.04457 0.03700 -0.0222 0.0670 1.0000
14.000 1.4220 0.04638 0.03891 -0.0217 0.0634 1.0000
14.250 1.4277 0.04837 0.04100 -0.0213 0.0602 1.0000
14.500 1.4339 0.05037 0.04310 -0.0210 0.0555 1.0000
14.750 1.4370 0.05276 0.04554 -0.0208 0.0500 1.0000
15.000 1.4368 0.05560 0.04839 -0.0208 0.0446 1.0000
15.250 1.4339 0.05881 0.05162 -0.0208 0.0403 1.0000
15.500 1.4303 0.06222 0.05509 -0.0211 0.0370 1.0000
15.750 1.4254 0.06590 0.05884 -0.0215 0.0340 1.0000
16.000 1.4194 0.06980 0.06283 -0.0221 0.0318 1.0000
16.250 1.4152 0.07357 0.06672 -0.0228 0.0293 1.0000
16.500 1.4081 0.07785 0.07112 -0.0237 0.0271 1.0000
16.750 1.4061 0.08149 0.07492 -0.0246 0.0180 1.0000
17.000 1.3875 0.08766 0.08115 -0.0265 0.0167 1.0000
17.250 1.3719 0.09360 0.08719 -0.0285 0.0158 1.0000
17.500 1.3570 0.09963 0.09335 -0.0308 0.0154 1.0000
17.750 1.3417 0.10589 0.09975 -0.0333 0.0151 1.0000
18.000 1.3256 0.11242 0.10643 -0.0360 0.0148 1.0000
18.250 1.3091 0.11921 0.11338 -0.0391 0.0147 1.0000
18.500 1.2916 0.12635 0.12069 -0.0425 0.0146 1.0000
18.750 1.2734 0.13380 0.12831 -0.0463 0.0145 1.0000
19.000 1.2544 0.14163 0.13630 -0.0504 0.0145 1.0000
19.250 1.2348 0.14983 0.14468 -0.0549 0.0146 1.0000
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