USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 200,000 Max Cl/Cd: 62 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa40b-il-200000-n5.txt Download as CSV file: xf-usa40b-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3209 0.09380 0.08991 -0.0360 1.0000 0.0377
-9.500 -0.3253 0.08988 0.08603 -0.0370 1.0000 0.0374
-9.000 -0.5480 0.04044 0.03576 -0.0739 0.9906 0.0351
-8.750 -0.5246 0.03648 0.03145 -0.0788 0.9839 0.0353
-8.500 -0.4984 0.03403 0.02876 -0.0816 0.9775 0.0358
-8.250 -0.4693 0.03172 0.02621 -0.0844 0.9718 0.0363
-8.000 -0.4425 0.02946 0.02365 -0.0864 0.9646 0.0369
-7.750 -0.4121 0.02722 0.02107 -0.0886 0.9586 0.0375
-7.500 -0.3835 0.02534 0.01888 -0.0899 0.9513 0.0379
-7.250 -0.3516 0.02367 0.01692 -0.0915 0.9448 0.0384
-7.000 -0.3187 0.02225 0.01523 -0.0929 0.9358 0.0388
-6.750 -0.2773 0.02093 0.01375 -0.0957 0.9255 0.0393
-6.500 -0.2399 0.01994 0.01270 -0.0976 0.9095 0.0399
-6.250 -0.2051 0.01912 0.01180 -0.0989 0.8943 0.0405
-6.000 -0.1715 0.01840 0.01100 -0.1000 0.8799 0.0413
-5.750 -0.1383 0.01772 0.01022 -0.1009 0.8640 0.0424
-5.500 -0.1063 0.01709 0.00945 -0.1015 0.8450 0.0435
-5.250 -0.0757 0.01649 0.00874 -0.1018 0.8235 0.0445
-5.000 -0.0460 0.01599 0.00818 -0.1020 0.8007 0.0454
-4.750 -0.0174 0.01558 0.00766 -0.1018 0.7781 0.0464
-4.500 0.0099 0.01523 0.00718 -0.1014 0.7573 0.0477
-4.250 0.0367 0.01492 0.00672 -0.1009 0.7377 0.0491
-4.000 0.0630 0.01463 0.00634 -0.1004 0.7193 0.0506
-3.750 0.0894 0.01443 0.00605 -0.0998 0.7020 0.0529
-3.500 0.1156 0.01424 0.00574 -0.0992 0.6845 0.0559
-3.250 0.1416 0.01404 0.00549 -0.0986 0.6662 0.0593
-3.000 0.1676 0.01385 0.00522 -0.0980 0.6469 0.0638
-2.750 0.1935 0.01367 0.00497 -0.0973 0.6255 0.0696
-2.500 0.2192 0.01350 0.00473 -0.0967 0.6019 0.0771
-2.250 0.2444 0.01336 0.00451 -0.0959 0.5753 0.0874
-2.000 0.2693 0.01325 0.00431 -0.0951 0.5453 0.1013
-1.750 0.2935 0.01316 0.00417 -0.0943 0.5132 0.1245
-1.500 0.3176 0.01310 0.00413 -0.0935 0.4825 0.1698
-1.250 0.3423 0.01311 0.00410 -0.0928 0.4563 0.2090
-1.000 0.3672 0.01308 0.00408 -0.0921 0.4345 0.2480
-0.750 0.3919 0.01303 0.00410 -0.0915 0.4156 0.2958
-0.500 0.4169 0.01301 0.00414 -0.0909 0.3991 0.3501
-0.250 0.4419 0.01299 0.00420 -0.0902 0.3849 0.4083
0.000 0.4663 0.01293 0.00430 -0.0894 0.3722 0.4792
0.250 0.4906 0.01289 0.00446 -0.0884 0.3618 0.5604
0.500 0.5144 0.01297 0.00464 -0.0873 0.3524 0.6244
0.750 0.5392 0.01306 0.00479 -0.0863 0.3438 0.6700
1.000 0.5637 0.01322 0.00492 -0.0853 0.3354 0.7044
1.250 0.5889 0.01337 0.00505 -0.0845 0.3278 0.7333
1.500 0.6141 0.01353 0.00516 -0.0837 0.3203 0.7543
1.750 0.6390 0.01372 0.00528 -0.0828 0.3140 0.7713
2.000 0.6644 0.01383 0.00540 -0.0821 0.3082 0.7883
2.250 0.6890 0.01396 0.00551 -0.0811 0.3025 0.8077
2.500 0.7132 0.01412 0.00563 -0.0802 0.2975 0.8288
2.750 0.7393 0.01420 0.00575 -0.0796 0.2926 0.8529
3.000 0.7677 0.01427 0.00586 -0.0794 0.2871 0.8859
3.250 0.8048 0.01444 0.00601 -0.0813 0.2817 1.0000
3.500 0.8310 0.01471 0.00620 -0.0810 0.2775 1.0000
3.750 0.8578 0.01495 0.00640 -0.0807 0.2732 1.0000
4.000 0.8840 0.01521 0.00661 -0.0803 0.2693 1.0000
4.250 0.9097 0.01550 0.00683 -0.0799 0.2657 1.0000
4.500 0.9349 0.01584 0.00708 -0.0794 0.2625 1.0000
4.750 0.9608 0.01612 0.00735 -0.0790 0.2594 1.0000
5.000 0.9867 0.01640 0.00762 -0.0786 0.2562 1.0000
5.250 1.0121 0.01669 0.00790 -0.0781 0.2530 1.0000
5.500 1.0371 0.01701 0.00817 -0.0775 0.2499 1.0000
5.750 1.0616 0.01736 0.00847 -0.0769 0.2470 1.0000
6.000 1.0861 0.01775 0.00880 -0.0764 0.2444 1.0000
6.250 1.1112 0.01806 0.00915 -0.0758 0.2420 1.0000
6.500 1.1360 0.01839 0.00951 -0.0753 0.2395 1.0000
6.750 1.1604 0.01874 0.00988 -0.0747 0.2372 1.0000
7.000 1.1845 0.01911 0.01024 -0.0741 0.2349 1.0000
7.250 1.2083 0.01949 0.01062 -0.0734 0.2329 1.0000
7.500 1.2319 0.01991 0.01102 -0.0727 0.2309 1.0000
7.750 1.2554 0.02040 0.01146 -0.0721 0.2291 1.0000
8.000 1.2790 0.02081 0.01193 -0.0714 0.2273 1.0000
8.250 1.3021 0.02121 0.01240 -0.0707 0.2253 1.0000
8.500 1.3246 0.02160 0.01286 -0.0699 0.2228 1.0000
8.750 1.3465 0.02200 0.01330 -0.0690 0.2204 1.0000
9.000 1.3681 0.02242 0.01376 -0.0681 0.2182 1.0000
9.250 1.3894 0.02287 0.01422 -0.0672 0.2163 1.0000
9.500 1.4109 0.02337 0.01472 -0.0663 0.2146 1.0000
9.750 1.4323 0.02393 0.01526 -0.0654 0.2127 1.0000
10.000 1.4516 0.02438 0.01585 -0.0642 0.2108 1.0000
10.250 1.4705 0.02487 0.01644 -0.0630 0.2087 1.0000
10.500 1.4885 0.02537 0.01703 -0.0616 0.2068 1.0000
10.750 1.5062 0.02590 0.01764 -0.0602 0.2052 1.0000
11.000 1.5232 0.02645 0.01826 -0.0587 0.2036 1.0000
11.250 1.5395 0.02700 0.01887 -0.0571 0.2019 1.0000
11.500 1.5554 0.02757 0.01947 -0.0556 0.2003 1.0000
11.750 1.5720 0.02820 0.02011 -0.0542 0.1985 1.0000
12.000 1.5862 0.02889 0.02089 -0.0526 0.1967 1.0000
12.250 1.5979 0.02960 0.02176 -0.0507 0.1948 1.0000
12.500 1.6097 0.03036 0.02266 -0.0489 0.1929 1.0000
12.750 1.6206 0.03114 0.02356 -0.0472 0.1908 1.0000
13.000 1.6313 0.03196 0.02447 -0.0455 0.1888 1.0000
13.250 1.6420 0.03283 0.02543 -0.0439 0.1871 1.0000
13.500 1.6529 0.03374 0.02640 -0.0424 0.1854 1.0000
13.750 1.6647 0.03468 0.02737 -0.0411 0.1838 1.0000
14.000 1.6720 0.03589 0.02872 -0.0397 0.1821 1.0000
14.250 1.6764 0.03730 0.03032 -0.0381 0.1800 1.0000
14.500 1.6800 0.03881 0.03199 -0.0368 0.1776 1.0000
14.750 1.6829 0.04038 0.03370 -0.0356 0.1749 1.0000
15.000 1.6862 0.04198 0.03537 -0.0346 0.1722 1.0000
15.250 1.6902 0.04358 0.03696 -0.0338 0.1693 1.0000
15.500 1.6851 0.04625 0.03988 -0.0333 0.1659 1.0000
15.750 1.6810 0.04896 0.04276 -0.0331 0.1621 1.0000
16.000 1.6779 0.05166 0.04553 -0.0330 0.1586 1.0000
16.250 1.6733 0.05468 0.04864 -0.0332 0.1554 1.0000
16.500 1.6633 0.05867 0.05285 -0.0340 0.1517 1.0000
16.750 1.6524 0.06294 0.05727 -0.0350 0.1481 1.0000
17.000 1.6407 0.06746 0.06186 -0.0364 0.1446 1.0000
17.250 1.6208 0.07353 0.06814 -0.0386 0.1410 1.0000
17.500 1.5931 0.08112 0.07593 -0.0418 0.1371 1.0000
17.750 1.5648 0.08910 0.08402 -0.0454 0.1332 1.0000
18.000 1.5150 0.10110 0.09625 -0.0512 0.1297 1.0000
18.250 1.4203 0.12182 0.11725 -0.0621 0.1248 1.0000
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