USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 500,000 Max Cl/Cd: 85.11 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa40b-il-500000.txt Download as CSV file: xf-usa40b-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3263 0.09109 0.08872 -0.0354 1.0000 0.0448
-9.250 -0.3207 0.08936 0.08703 -0.0345 1.0000 0.0452
-9.000 -0.5348 0.04149 0.03837 -0.0761 0.9917 0.0393
-8.750 -0.5054 0.03974 0.03665 -0.0784 0.9881 0.0397
-8.500 -0.4837 0.03274 0.02917 -0.0851 0.9833 0.0377
-8.250 -0.4600 0.02774 0.02362 -0.0890 0.9769 0.0376
-8.000 -0.4265 0.02421 0.01965 -0.0926 0.9720 0.0375
-7.750 -0.3900 0.02179 0.01691 -0.0955 0.9666 0.0376
-7.500 -0.3550 0.02000 0.01487 -0.0974 0.9595 0.0378
-7.250 -0.3159 0.01852 0.01318 -0.0999 0.9558 0.0381
-7.000 -0.2857 0.01748 0.01197 -0.1005 0.9470 0.0385
-6.750 -0.2479 0.01652 0.01086 -0.1024 0.9413 0.0388
-6.500 -0.2161 0.01536 0.00961 -0.1033 0.9306 0.0394
-6.250 -0.1801 0.01451 0.00875 -0.1049 0.9201 0.0401
-6.000 -0.1447 0.01391 0.00810 -0.1062 0.9066 0.0409
-5.750 -0.1140 0.01338 0.00748 -0.1065 0.8883 0.0415
-5.500 -0.0859 0.01293 0.00694 -0.1062 0.8665 0.0422
-5.250 -0.0588 0.01253 0.00643 -0.1058 0.8415 0.0429
-5.000 -0.0324 0.01221 0.00596 -0.1051 0.8146 0.0435
-4.750 -0.0066 0.01195 0.00555 -0.1043 0.7876 0.0442
-4.500 0.0180 0.01151 0.00501 -0.1035 0.7648 0.0453
-4.250 0.0437 0.01130 0.00472 -0.1028 0.7457 0.0465
-4.000 0.0698 0.01114 0.00447 -0.1021 0.7282 0.0479
-3.750 0.0962 0.01102 0.00424 -0.1015 0.7119 0.0496
-3.500 0.1221 0.01074 0.00393 -0.1009 0.6969 0.0517
-3.250 0.1485 0.01061 0.00374 -0.1003 0.6821 0.0542
-3.000 0.1748 0.01044 0.00350 -0.0996 0.6659 0.0575
-2.750 0.2012 0.01031 0.00333 -0.0990 0.6477 0.0623
-2.500 0.2273 0.01015 0.00313 -0.0984 0.6267 0.0704
-2.250 0.2532 0.00998 0.00293 -0.0977 0.6019 0.0830
-2.000 0.2783 0.00987 0.00276 -0.0970 0.5731 0.0987
-1.750 0.3031 0.00976 0.00264 -0.0962 0.5390 0.1285
-1.500 0.3273 0.00971 0.00263 -0.0954 0.5016 0.1868
-1.250 0.3521 0.00981 0.00263 -0.0946 0.4661 0.2169
-1.000 0.3772 0.00988 0.00264 -0.0940 0.4365 0.2444
-0.750 0.4026 0.00991 0.00266 -0.0934 0.4133 0.2809
-0.500 0.4281 0.00987 0.00271 -0.0928 0.3950 0.3433
-0.250 0.4537 0.00978 0.00277 -0.0923 0.3800 0.4204
0.000 0.4787 0.00965 0.00286 -0.0917 0.3672 0.5125
0.250 0.5033 0.00961 0.00301 -0.0908 0.3554 0.6017
0.500 0.5292 0.00966 0.00314 -0.0901 0.3454 0.6552
1.000 0.5809 0.00990 0.00338 -0.0886 0.3278 0.7166
1.250 0.6065 0.01006 0.00351 -0.0879 0.3200 0.7381
1.500 0.6328 0.01018 0.00362 -0.0873 0.3134 0.7557
1.750 0.6587 0.01030 0.00373 -0.0866 0.3069 0.7732
2.000 0.6837 0.01050 0.00387 -0.0857 0.3003 0.7895
2.250 0.7101 0.01057 0.00396 -0.0852 0.2953 0.8046
2.500 0.7357 0.01067 0.00406 -0.0844 0.2897 0.8191
2.750 0.7601 0.01083 0.00419 -0.0835 0.2839 0.8352
3.000 0.7857 0.01090 0.00429 -0.0828 0.2796 0.8513
3.250 0.8109 0.01093 0.00438 -0.0820 0.2752 0.8723
3.500 0.8410 0.01094 0.00449 -0.0823 0.2707 0.9177
3.750 0.8781 0.01124 0.00471 -0.0843 0.2654 1.0000
4.000 0.9056 0.01138 0.00485 -0.0841 0.2624 1.0000
4.250 0.9325 0.01156 0.00500 -0.0838 0.2589 1.0000
4.500 0.9588 0.01177 0.00517 -0.0834 0.2555 1.0000
4.750 0.9844 0.01205 0.00538 -0.0829 0.2521 1.0000
5.000 1.0095 0.01237 0.00565 -0.0823 0.2486 1.0000
5.250 1.0361 0.01254 0.00583 -0.0820 0.2463 1.0000
5.500 1.0622 0.01273 0.00602 -0.0815 0.2435 1.0000
5.750 1.0878 0.01295 0.00622 -0.0810 0.2407 1.0000
6.000 1.1129 0.01321 0.00645 -0.0805 0.2380 1.0000
6.250 1.1373 0.01355 0.00674 -0.0798 0.2353 1.0000
6.500 1.1617 0.01393 0.00710 -0.0792 0.2327 1.0000
6.750 1.1872 0.01412 0.00732 -0.0786 0.2309 1.0000
7.000 1.2123 0.01433 0.00756 -0.0781 0.2286 1.0000
7.250 1.2371 0.01457 0.00781 -0.0775 0.2264 1.0000
7.500 1.2614 0.01482 0.00805 -0.0768 0.2240 1.0000
7.750 1.2851 0.01512 0.00834 -0.0761 0.2218 1.0000
8.000 1.3083 0.01553 0.00872 -0.0753 0.2195 1.0000
8.250 1.3317 0.01601 0.00919 -0.0746 0.2174 1.0000
8.500 1.3556 0.01624 0.00948 -0.0739 0.2162 1.0000
8.750 1.3791 0.01650 0.00979 -0.0731 0.2146 1.0000
9.000 1.4022 0.01677 0.01009 -0.0723 0.2127 1.0000
9.250 1.4248 0.01704 0.01040 -0.0714 0.2107 1.0000
9.500 1.4471 0.01735 0.01073 -0.0705 0.2090 1.0000
9.750 1.4688 0.01769 0.01108 -0.0695 0.2073 1.0000
10.000 1.4899 0.01810 0.01148 -0.0685 0.2053 1.0000
10.250 1.5116 0.01871 0.01208 -0.0677 0.2031 1.0000
10.500 1.5324 0.01907 0.01251 -0.0666 0.2020 1.0000
10.750 1.5517 0.01937 0.01289 -0.0652 0.2008 1.0000
11.000 1.5704 0.01971 0.01329 -0.0637 0.1995 1.0000
11.250 1.5887 0.02007 0.01372 -0.0622 0.1981 1.0000
11.500 1.6063 0.02042 0.01412 -0.0607 0.1964 1.0000
11.750 1.6226 0.02074 0.01448 -0.0589 0.1943 1.0000
12.000 1.6379 0.02109 0.01484 -0.0571 0.1919 1.0000
12.250 1.6539 0.02170 0.01543 -0.0556 0.1891 1.0000
12.500 1.6686 0.02212 0.01594 -0.0538 0.1871 1.0000
12.750 1.6831 0.02250 0.01642 -0.0521 0.1850 1.0000
13.000 1.6974 0.02292 0.01693 -0.0504 0.1826 1.0000
13.250 1.7112 0.02340 0.01747 -0.0488 0.1801 1.0000
13.500 1.7238 0.02401 0.01810 -0.0471 0.1777 1.0000
13.750 1.7351 0.02483 0.01892 -0.0454 0.1751 1.0000
14.000 1.7480 0.02548 0.01969 -0.0440 0.1729 1.0000
14.250 1.7609 0.02613 0.02045 -0.0426 0.1702 1.0000
14.500 1.7729 0.02689 0.02129 -0.0413 0.1672 1.0000
14.750 1.7822 0.02787 0.02229 -0.0399 0.1640 1.0000
15.000 1.7895 0.02907 0.02353 -0.0385 0.1609 1.0000
15.250 1.8023 0.02996 0.02455 -0.0376 0.1575 1.0000
15.500 1.8111 0.03116 0.02583 -0.0366 0.1534 1.0000
15.750 1.8152 0.03281 0.02749 -0.0355 0.1497 1.0000
16.000 1.8241 0.03418 0.02897 -0.0348 0.1458 1.0000
16.250 1.8294 0.03590 0.03077 -0.0341 0.1408 1.0000
16.500 1.8294 0.03819 0.03309 -0.0335 0.1361 1.0000
16.750 1.8315 0.04039 0.03537 -0.0331 0.1294 1.0000
17.000 1.8267 0.04337 0.03840 -0.0328 0.1235 1.0000
17.250 1.8185 0.04686 0.04193 -0.0329 0.1164 1.0000
17.500 1.8065 0.05095 0.04608 -0.0332 0.1102 1.0000
18.000 1.7685 0.06158 0.05687 -0.0355 0.1004 1.0000
18.250 1.7442 0.06805 0.06343 -0.0375 0.0969 1.0000
18.500 1.7160 0.07538 0.07088 -0.0401 0.0944 1.0000
18.750 1.6900 0.08264 0.07827 -0.0428 0.0920 1.0000
19.000 1.6607 0.09059 0.08635 -0.0461 0.0900 1.0000
19.250 1.6298 0.09900 0.09487 -0.0497 0.0881 1.0000
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