USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.13 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa40b-il-1000000.txt Download as CSV file: xf-usa40b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 40 B 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6289 0.07041 0.06825 -0.0556 1.0000 0.0265
-12.500 -0.7261 0.04879 0.04627 -0.0742 1.0000 0.0260
-12.250 -0.7625 0.04140 0.03869 -0.0805 1.0000 0.0260
-12.000 -0.8065 0.03722 0.03438 -0.0801 1.0000 0.0260
-11.750 -0.8201 0.03460 0.03159 -0.0789 1.0000 0.0260
-11.500 -0.8107 0.03208 0.02886 -0.0804 0.9989 0.0261
-11.250 -0.7835 0.03005 0.02661 -0.0837 0.9966 0.0262
-11.000 -0.7639 0.02538 0.02154 -0.0880 0.9939 0.0265
-10.750 -0.7371 0.02344 0.01948 -0.0898 0.9917 0.0268
-10.500 -0.7085 0.02218 0.01814 -0.0911 0.9891 0.0270
-10.250 -0.6776 0.02116 0.01705 -0.0926 0.9868 0.0272
-10.000 -0.6450 0.02034 0.01617 -0.0942 0.9849 0.0275
-9.750 -0.6114 0.01951 0.01527 -0.0959 0.9834 0.0278
-9.500 -0.5772 0.01871 0.01440 -0.0976 0.9823 0.0281
-9.250 -0.5497 0.01787 0.01348 -0.0979 0.9779 0.0283
-9.000 -0.5168 0.01703 0.01256 -0.0992 0.9743 0.0286
-8.750 -0.4803 0.01614 0.01159 -0.1011 0.9714 0.0288
-8.500 -0.4469 0.01536 0.01073 -0.1023 0.9658 0.0291
-8.250 -0.4122 0.01465 0.00995 -0.1037 0.9584 0.0294
-8.000 -0.3772 0.01402 0.00925 -0.1052 0.9501 0.0296
-7.750 -0.3405 0.01347 0.00863 -0.1069 0.9417 0.0298
-7.500 -0.3061 0.01301 0.00809 -0.1081 0.9295 0.0300
-7.250 -0.2751 0.01216 0.00714 -0.1089 0.9140 0.0304
-7.000 -0.2470 0.01156 0.00647 -0.1089 0.8960 0.0309
-6.750 -0.2202 0.01120 0.00603 -0.1085 0.8745 0.0313
-6.500 -0.1944 0.01095 0.00568 -0.1078 0.8488 0.0317
-6.250 -0.1697 0.01077 0.00536 -0.1069 0.8143 0.0321
-6.000 -0.1455 0.01066 0.00508 -0.1058 0.7779 0.0327
-5.750 -0.1206 0.01049 0.00478 -0.1050 0.7516 0.0331
-5.500 -0.0948 0.01032 0.00451 -0.1043 0.7328 0.0335
-5.250 -0.0685 0.01016 0.00426 -0.1037 0.7181 0.0339
-5.000 -0.0421 0.01003 0.00404 -0.1031 0.7035 0.0343
-4.750 -0.0158 0.00968 0.00363 -0.1026 0.6901 0.0350
-4.500 0.0110 0.00947 0.00338 -0.1022 0.6778 0.0359
-4.250 0.0379 0.00934 0.00319 -0.1017 0.6647 0.0367
-4.000 0.0652 0.00921 0.00301 -0.1013 0.6505 0.0376
-3.750 0.0924 0.00911 0.00285 -0.1008 0.6339 0.0386
-3.500 0.1191 0.00899 0.00264 -0.1003 0.6141 0.0399
-3.250 0.1455 0.00891 0.00249 -0.0997 0.5905 0.0416
-3.000 0.1722 0.00890 0.00238 -0.0992 0.5635 0.0437
-2.750 0.1982 0.00888 0.00226 -0.0986 0.5317 0.0472
-2.500 0.2239 0.00892 0.00217 -0.0979 0.4956 0.0530
-2.250 0.2497 0.00899 0.00213 -0.0973 0.4599 0.0632
-2.000 0.2758 0.00904 0.00210 -0.0967 0.4298 0.0741
-1.750 0.3023 0.00908 0.00206 -0.0962 0.4070 0.0838
-1.500 0.3290 0.00908 0.00203 -0.0958 0.3885 0.0962
-1.000 0.3823 0.00889 0.00201 -0.0950 0.3597 0.1814
-0.750 0.4095 0.00889 0.00203 -0.0947 0.3481 0.2048
-0.500 0.4365 0.00894 0.00205 -0.0943 0.3361 0.2236
-0.250 0.4640 0.00892 0.00206 -0.0940 0.3276 0.2452
0.000 0.4907 0.00890 0.00209 -0.0936 0.3182 0.2855
0.250 0.5175 0.00873 0.00213 -0.0933 0.3119 0.3669
0.500 0.5440 0.00863 0.00219 -0.0929 0.3045 0.4381
0.750 0.5701 0.00847 0.00227 -0.0924 0.2981 0.5359
1.000 0.5969 0.00843 0.00236 -0.0920 0.2924 0.5974
1.250 0.6234 0.00848 0.00246 -0.0914 0.2857 0.6411
1.500 0.6503 0.00853 0.00256 -0.0910 0.2802 0.6758
1.750 0.6775 0.00860 0.00264 -0.0905 0.2749 0.6969
2.000 0.7042 0.00872 0.00275 -0.0901 0.2690 0.7151
2.250 0.7311 0.00883 0.00285 -0.0896 0.2643 0.7326
2.500 0.7582 0.00890 0.00294 -0.0892 0.2605 0.7469
2.750 0.7849 0.00901 0.00304 -0.0887 0.2560 0.7600
3.000 0.8112 0.00916 0.00316 -0.0882 0.2509 0.7724
3.250 0.8380 0.00926 0.00327 -0.0877 0.2477 0.7847
3.500 0.8647 0.00934 0.00338 -0.0873 0.2447 0.7953
3.750 0.8913 0.00945 0.00348 -0.0868 0.2413 0.8060
4.000 0.9173 0.00958 0.00361 -0.0862 0.2376 0.8172
4.250 0.9423 0.00975 0.00377 -0.0855 0.2332 0.8297
4.500 0.9687 0.00979 0.00387 -0.0850 0.2314 0.8445
4.750 0.9942 0.00983 0.00398 -0.0843 0.2290 0.8661
5.000 1.0330 0.00979 0.00412 -0.0866 0.2259 1.0000
5.250 1.0594 0.00997 0.00427 -0.0862 0.2232 1.0000
5.500 1.0849 0.01021 0.00446 -0.0856 0.2194 1.0000
5.750 1.1109 0.01039 0.00463 -0.0852 0.2169 1.0000
6.000 1.1375 0.01053 0.00477 -0.0848 0.2154 1.0000
6.250 1.1638 0.01068 0.00493 -0.0844 0.2136 1.0000
6.500 1.1898 0.01085 0.00509 -0.0840 0.2114 1.0000
6.750 1.2153 0.01105 0.00526 -0.0834 0.2091 1.0000
7.000 1.2402 0.01127 0.00547 -0.0828 0.2066 1.0000
7.250 1.2641 0.01157 0.00574 -0.0821 0.2037 1.0000
7.500 1.2890 0.01177 0.00595 -0.0815 0.2021 1.0000
7.750 1.3147 0.01193 0.00613 -0.0810 0.2009 1.0000
8.000 1.3399 0.01210 0.00632 -0.0805 0.1995 1.0000
8.250 1.3647 0.01229 0.00653 -0.0799 0.1981 1.0000
8.500 1.3891 0.01250 0.00674 -0.0792 0.1964 1.0000
8.750 1.4131 0.01272 0.00697 -0.0785 0.1947 1.0000
9.000 1.4365 0.01297 0.00722 -0.0777 0.1928 1.0000
9.250 1.4587 0.01328 0.00752 -0.0767 0.1906 1.0000
9.500 1.4798 0.01364 0.00789 -0.0756 0.1882 1.0000
9.750 1.5037 0.01382 0.00811 -0.0749 0.1874 1.0000
10.000 1.5270 0.01402 0.00835 -0.0741 0.1864 1.0000
10.250 1.5498 0.01424 0.00860 -0.0732 0.1853 1.0000
10.500 1.5720 0.01447 0.00886 -0.0722 0.1839 1.0000
10.750 1.5934 0.01468 0.00909 -0.0711 0.1820 1.0000
11.000 1.6131 0.01492 0.00934 -0.0697 0.1795 1.0000
11.250 1.6307 0.01526 0.00968 -0.0680 0.1770 1.0000
11.500 1.6467 0.01567 0.01009 -0.0661 0.1744 1.0000
11.750 1.6685 0.01582 0.01031 -0.0651 0.1728 1.0000
12.000 1.6892 0.01603 0.01055 -0.0640 0.1706 1.0000
12.250 1.7081 0.01631 0.01086 -0.0626 0.1684 1.0000
12.500 1.7258 0.01666 0.01122 -0.0611 0.1658 1.0000
12.750 1.7413 0.01711 0.01167 -0.0594 0.1629 1.0000
13.000 1.7582 0.01750 0.01210 -0.0578 0.1606 1.0000
13.250 1.7772 0.01780 0.01246 -0.0567 0.1582 1.0000
13.500 1.7943 0.01819 0.01288 -0.0552 0.1550 1.0000
13.750 1.8087 0.01873 0.01342 -0.0536 0.1514 1.0000
14.000 1.8230 0.01929 0.01401 -0.0519 0.1479 1.0000
14.250 1.8388 0.01978 0.01455 -0.0505 0.1441 1.0000
14.500 1.8494 0.02058 0.01532 -0.0487 0.1377 1.0000
14.750 1.8618 0.02130 0.01607 -0.0471 0.1318 1.0000
15.000 1.8691 0.02237 0.01711 -0.0451 0.1242 1.0000
15.250 1.8724 0.02373 0.01844 -0.0429 0.1138 1.0000
15.500 1.8698 0.02559 0.02025 -0.0406 0.1019 1.0000
15.750 1.8659 0.02768 0.02232 -0.0385 0.0939 1.0000
16.000 1.8648 0.02969 0.02437 -0.0369 0.0893 1.0000
16.250 1.8616 0.03205 0.02676 -0.0356 0.0851 1.0000
16.500 1.8615 0.03426 0.02904 -0.0347 0.0822 1.0000
16.750 1.8580 0.03692 0.03175 -0.0339 0.0797 1.0000
17.000 1.8506 0.04008 0.03498 -0.0334 0.0768 1.0000
17.250 1.8489 0.04281 0.03779 -0.0332 0.0747 1.0000
17.500 1.8425 0.04612 0.04120 -0.0332 0.0724 1.0000
17.750 1.8303 0.05027 0.04543 -0.0336 0.0702 1.0000
18.000 1.8153 0.05497 0.05022 -0.0343 0.0681 1.0000
18.250 1.8049 0.05928 0.05464 -0.0352 0.0662 1.0000
18.500 1.7871 0.06477 0.06024 -0.0367 0.0639 1.0000
18.750 1.7609 0.07165 0.06724 -0.0389 0.0620 1.0000
19.000 1.7314 0.07930 0.07502 -0.0416 0.0606 1.0000
19.250 1.7041 0.08681 0.08268 -0.0445 0.0591 1.0000
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