BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 500,000 Max Cl/Cd: 81.07 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-boe103-il-500000-n5.txt Download as CSV file: xf-boe103-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7897 0.04313 0.04006 -0.0837 1.0000 0.0158
-12.500 -0.8271 0.03932 0.03609 -0.0816 1.0000 0.0158
-12.250 -0.8522 0.03747 0.03413 -0.0763 1.0000 0.0159
-12.000 -0.8413 0.03493 0.03137 -0.0775 0.9972 0.0163
-11.750 -0.8241 0.03214 0.02827 -0.0796 0.9940 0.0169
-11.500 -0.8094 0.02920 0.02493 -0.0806 0.9891 0.0176
-11.250 -0.7858 0.02737 0.02284 -0.0820 0.9859 0.0181
-11.000 -0.7569 0.02666 0.02209 -0.0832 0.9830 0.0184
-10.750 -0.7298 0.02604 0.02142 -0.0839 0.9783 0.0187
-10.500 -0.7000 0.02529 0.02059 -0.0852 0.9751 0.0191
-10.250 -0.6730 0.02442 0.01961 -0.0859 0.9710 0.0195
-10.000 -0.6475 0.02353 0.01859 -0.0863 0.9655 0.0200
-9.750 -0.6191 0.02254 0.01741 -0.0872 0.9619 0.0207
-9.500 -0.5951 0.02164 0.01632 -0.0870 0.9547 0.0213
-9.250 -0.5664 0.02083 0.01532 -0.0877 0.9499 0.0218
-9.000 -0.5401 0.01971 0.01408 -0.0880 0.9440 0.0223
-8.750 -0.5120 0.01899 0.01332 -0.0885 0.9376 0.0227
-8.500 -0.4817 0.01841 0.01268 -0.0894 0.9323 0.0232
-8.250 -0.4543 0.01785 0.01205 -0.0895 0.9245 0.0238
-8.000 -0.4250 0.01722 0.01130 -0.0901 0.9178 0.0243
-7.750 -0.3983 0.01661 0.01059 -0.0900 0.9095 0.0248
-7.500 -0.3703 0.01608 0.00994 -0.0901 0.9018 0.0254
-7.250 -0.3439 0.01563 0.00939 -0.0899 0.8933 0.0260
-7.000 -0.3166 0.01520 0.00885 -0.0898 0.8853 0.0264
-6.750 -0.2905 0.01481 0.00835 -0.0894 0.8767 0.0266
-6.250 -0.2402 0.01348 0.00692 -0.0886 0.8601 0.0277
-5.750 -0.1881 0.01273 0.00608 -0.0879 0.8437 0.0289
-5.250 -0.1357 0.01206 0.00529 -0.0871 0.8267 0.0298
-5.000 -0.1093 0.01177 0.00493 -0.0868 0.8186 0.0302
-4.750 -0.0829 0.01148 0.00461 -0.0864 0.8097 0.0307
-4.500 -0.0564 0.01124 0.00430 -0.0860 0.8011 0.0312
-4.250 -0.0298 0.01101 0.00403 -0.0857 0.7917 0.0317
-4.000 -0.0030 0.01084 0.00379 -0.0854 0.7832 0.0322
-3.750 0.0233 0.01057 0.00348 -0.0850 0.7735 0.0331
-3.500 0.0499 0.01036 0.00323 -0.0847 0.7638 0.0339
-3.250 0.0764 0.01021 0.00301 -0.0843 0.7527 0.0347
-3.000 0.1029 0.01008 0.00282 -0.0839 0.7397 0.0356
-2.750 0.1294 0.00998 0.00266 -0.0835 0.7257 0.0367
-2.500 0.1560 0.00990 0.00250 -0.0831 0.7120 0.0379
-2.250 0.1825 0.00983 0.00237 -0.0826 0.6981 0.0396
-2.000 0.2087 0.00975 0.00225 -0.0822 0.6834 0.0443
-1.750 0.2341 0.00950 0.00213 -0.0817 0.6700 0.0884
-1.500 0.2602 0.00935 0.00208 -0.0814 0.6588 0.1255
-1.250 0.2871 0.00927 0.00203 -0.0811 0.6487 0.1484
-1.000 0.3136 0.00921 0.00200 -0.0808 0.6384 0.1716
-0.750 0.3401 0.00910 0.00196 -0.0805 0.6282 0.2049
-0.500 0.3663 0.00894 0.00193 -0.0802 0.6192 0.2573
-0.250 0.3910 0.00860 0.00193 -0.0798 0.6093 0.3791
0.000 0.4159 0.00830 0.00195 -0.0793 0.5994 0.4906
0.250 0.4395 0.00802 0.00200 -0.0785 0.5883 0.6082
0.500 0.4633 0.00786 0.00207 -0.0775 0.5757 0.6926
0.750 0.4870 0.00775 0.00213 -0.0765 0.5613 0.7609
1.000 0.5090 0.00764 0.00224 -0.0749 0.5463 0.8444
1.250 0.5339 0.00766 0.00235 -0.0738 0.5314 0.9125
1.500 0.5660 0.00779 0.00244 -0.0745 0.5155 0.9465
1.750 0.6009 0.00795 0.00251 -0.0760 0.4979 0.9675
2.250 0.6759 0.00839 0.00270 -0.0803 0.4491 0.9943
2.500 0.7094 0.00875 0.00284 -0.0818 0.4090 1.0000
2.750 0.7279 0.00911 0.00299 -0.0800 0.3725 1.0000
3.000 0.7471 0.00945 0.00315 -0.0784 0.3432 1.0000
3.250 0.7674 0.00976 0.00332 -0.0769 0.3208 1.0000
3.750 0.8106 0.01030 0.00365 -0.0746 0.2860 1.0000
4.000 0.8338 0.01052 0.00381 -0.0737 0.2730 1.0000
4.250 0.8570 0.01075 0.00398 -0.0729 0.2607 1.0000
4.500 0.8802 0.01100 0.00416 -0.0720 0.2474 1.0000
4.750 0.9031 0.01127 0.00436 -0.0712 0.2327 1.0000
5.000 0.9257 0.01158 0.00458 -0.0703 0.2158 1.0000
5.250 0.9478 0.01193 0.00483 -0.0693 0.1969 1.0000
5.500 0.9693 0.01233 0.00511 -0.0683 0.1774 1.0000
5.750 0.9905 0.01274 0.00542 -0.0672 0.1583 1.0000
6.000 1.0111 0.01320 0.00576 -0.0661 0.1387 1.0000
6.250 1.0315 0.01366 0.00613 -0.0649 0.1223 1.0000
6.500 1.0530 0.01404 0.00646 -0.0640 0.1122 1.0000
6.750 1.0747 0.01440 0.00679 -0.0630 0.1060 1.0000
7.000 1.0967 0.01474 0.00711 -0.0621 0.1016 1.0000
7.250 1.1180 0.01510 0.00746 -0.0611 0.0978 1.0000
7.500 1.1393 0.01545 0.00781 -0.0602 0.0949 1.0000
7.750 1.1604 0.01576 0.00815 -0.0591 0.0932 1.0000
8.000 1.1805 0.01609 0.00851 -0.0579 0.0915 1.0000
8.250 1.2002 0.01645 0.00889 -0.0567 0.0896 1.0000
8.500 1.2189 0.01687 0.00931 -0.0553 0.0869 1.0000
8.750 1.2368 0.01735 0.00979 -0.0539 0.0837 1.0000
9.000 1.2558 0.01776 0.01023 -0.0526 0.0816 1.0000
9.250 1.2749 0.01816 0.01067 -0.0514 0.0791 1.0000
9.500 1.2930 0.01863 0.01116 -0.0502 0.0762 1.0000
9.750 1.3098 0.01918 0.01171 -0.0488 0.0732 1.0000
10.000 1.3264 0.01975 0.01230 -0.0474 0.0707 1.0000
10.250 1.3445 0.02023 0.01283 -0.0462 0.0686 1.0000
10.500 1.3613 0.02079 0.01342 -0.0450 0.0648 1.0000
10.750 1.3765 0.02148 0.01410 -0.0436 0.0601 1.0000
11.000 1.3901 0.02228 0.01488 -0.0421 0.0514 1.0000
11.250 1.3982 0.02347 0.01597 -0.0401 0.0408 1.0000
11.500 1.4087 0.02454 0.01705 -0.0384 0.0369 1.0000
11.750 1.4189 0.02564 0.01818 -0.0369 0.0341 1.0000
12.000 1.4291 0.02680 0.01937 -0.0354 0.0316 1.0000
12.250 1.4390 0.02801 0.02063 -0.0340 0.0290 1.0000
12.500 1.4467 0.02942 0.02208 -0.0326 0.0265 1.0000
12.750 1.4569 0.03067 0.02339 -0.0315 0.0162 1.0000
13.000 1.4564 0.03287 0.02557 -0.0298 0.0132 1.0000
13.250 1.4607 0.03473 0.02752 -0.0285 0.0122 1.0000
13.500 1.4642 0.03674 0.02963 -0.0274 0.0114 1.0000
13.750 1.4698 0.03860 0.03159 -0.0266 0.0109 1.0000
14.000 1.4741 0.04063 0.03372 -0.0258 0.0104 1.0000
14.250 1.4768 0.04290 0.03609 -0.0251 0.0099 1.0000
14.500 1.4778 0.04541 0.03871 -0.0245 0.0095 1.0000
14.750 1.4769 0.04821 0.04162 -0.0241 0.0092 1.0000
15.000 1.4779 0.05089 0.04441 -0.0239 0.0090 1.0000
15.250 1.4786 0.05369 0.04732 -0.0238 0.0087 1.0000
15.500 1.4780 0.05672 0.05046 -0.0239 0.0085 1.0000
15.750 1.4758 0.06001 0.05387 -0.0242 0.0083 1.0000
16.000 1.4725 0.06355 0.05753 -0.0246 0.0081 1.0000
16.250 1.4679 0.06736 0.06145 -0.0252 0.0080 1.0000
16.500 1.4617 0.07144 0.06566 -0.0259 0.0078 1.0000
16.750 1.4538 0.07587 0.07021 -0.0269 0.0077 1.0000
17.000 1.4445 0.08063 0.07510 -0.0282 0.0076 1.0000
17.250 1.4335 0.08575 0.08035 -0.0296 0.0075 1.0000
17.500 1.4208 0.09124 0.08598 -0.0314 0.0074 1.0000
17.750 1.4066 0.09710 0.09198 -0.0334 0.0073 1.0000
18.000 1.3908 0.10337 0.09838 -0.0357 0.0073 1.0000
18.250 1.3740 0.10994 0.10509 -0.0383 0.0072 1.0000
18.500 1.3562 0.11674 0.11203 -0.0411 0.0072 1.0000
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Polar data table (+)
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