USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 500,000 Max Cl/Cd: 88.36 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa40b-il-500000-n5.txt Download as CSV file: xf-usa40b-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7355 0.04509 0.04162 -0.0765 1.0000 0.0256
-12.000 -0.7740 0.03916 0.03551 -0.0799 1.0000 0.0255
-11.750 -0.7993 0.03564 0.03182 -0.0800 1.0000 0.0256
-11.500 -0.7902 0.03258 0.02850 -0.0826 0.9979 0.0257
-11.250 -0.7666 0.02989 0.02554 -0.0863 0.9942 0.0259
-11.000 -0.7427 0.02791 0.02334 -0.0885 0.9907 0.0260
-10.750 -0.7168 0.02624 0.02146 -0.0903 0.9869 0.0262
-10.500 -0.6880 0.02483 0.01986 -0.0921 0.9839 0.0263
-10.250 -0.6608 0.02332 0.01823 -0.0935 0.9806 0.0265
-10.000 -0.6350 0.02211 0.01692 -0.0941 0.9758 0.0267
-9.500 -0.5734 0.02020 0.01487 -0.0967 0.9697 0.0271
-9.250 -0.5482 0.01943 0.01405 -0.0967 0.9630 0.0273
-9.000 -0.5173 0.01865 0.01319 -0.0977 0.9589 0.0275
-8.750 -0.4863 0.01793 0.01241 -0.0986 0.9542 0.0278
-8.500 -0.4561 0.01726 0.01168 -0.0993 0.9476 0.0281
-8.250 -0.4181 0.01657 0.01091 -0.1014 0.9419 0.0285
-8.000 -0.3807 0.01590 0.01016 -0.1034 0.9288 0.0289
-7.750 -0.3384 0.01523 0.00935 -0.1064 0.9097 0.0293
-7.500 -0.3044 0.01469 0.00867 -0.1075 0.8846 0.0296
-7.250 -0.2757 0.01427 0.00811 -0.1076 0.8576 0.0299
-7.000 -0.2490 0.01392 0.00761 -0.1071 0.8294 0.0301
-6.750 -0.2241 0.01357 0.00710 -0.1064 0.7958 0.0304
-6.500 -0.1999 0.01323 0.00661 -0.1055 0.7659 0.0307
-6.000 -0.1498 0.01273 0.00589 -0.1041 0.7258 0.0315
-5.750 -0.1239 0.01250 0.00557 -0.1035 0.7103 0.0319
-5.500 -0.0978 0.01228 0.00527 -0.1030 0.6957 0.0323
-5.250 -0.0715 0.01208 0.00499 -0.1025 0.6818 0.0329
-5.000 -0.0452 0.01189 0.00472 -0.1019 0.6669 0.0334
-4.750 -0.0185 0.01171 0.00445 -0.1015 0.6516 0.0340
-4.500 0.0079 0.01154 0.00421 -0.1009 0.6344 0.0347
-4.250 0.0343 0.01136 0.00397 -0.1004 0.6161 0.0357
-4.000 0.0606 0.01123 0.00376 -0.0999 0.5961 0.0366
-3.750 0.0867 0.01115 0.00357 -0.0993 0.5717 0.0377
-3.500 0.1124 0.01112 0.00339 -0.0986 0.5405 0.0388
-3.250 0.1378 0.01111 0.00324 -0.0979 0.5061 0.0403
-3.000 0.1634 0.01113 0.00312 -0.0972 0.4737 0.0423
-2.750 0.1893 0.01115 0.00302 -0.0966 0.4465 0.0451
-2.500 0.2155 0.01116 0.00295 -0.0961 0.4238 0.0495
-2.250 0.2419 0.01117 0.00289 -0.0956 0.4038 0.0565
-2.000 0.2684 0.01118 0.00285 -0.0951 0.3858 0.0652
-1.500 0.3222 0.01118 0.00276 -0.0943 0.3580 0.0819
-1.250 0.3491 0.01117 0.00272 -0.0939 0.3477 0.0918
-1.000 0.3760 0.01111 0.00269 -0.0936 0.3380 0.1108
-0.750 0.4025 0.01100 0.00270 -0.0932 0.3294 0.1579
-0.500 0.4295 0.01098 0.00272 -0.0929 0.3207 0.1900
-0.250 0.4563 0.01099 0.00275 -0.0925 0.3129 0.2144
0.000 0.4833 0.01094 0.00277 -0.0921 0.3060 0.2441
0.250 0.5099 0.01087 0.00281 -0.0918 0.2994 0.2908
0.500 0.5364 0.01076 0.00288 -0.0914 0.2941 0.3645
0.750 0.5631 0.01070 0.00294 -0.0911 0.2886 0.4161
1.000 0.5894 0.01065 0.00301 -0.0906 0.2828 0.4729
1.250 0.6154 0.01061 0.00312 -0.0901 0.2778 0.5406
1.500 0.6417 0.01060 0.00324 -0.0895 0.2727 0.5963
1.750 0.6679 0.01066 0.00336 -0.0890 0.2673 0.6373
2.000 0.6937 0.01076 0.00350 -0.0883 0.2625 0.6714
2.250 0.7202 0.01084 0.00362 -0.0878 0.2590 0.6982
2.500 0.7466 0.01094 0.00374 -0.0872 0.2550 0.7182
2.750 0.7729 0.01107 0.00386 -0.0867 0.2510 0.7354
3.000 0.7987 0.01121 0.00399 -0.0861 0.2472 0.7488
3.250 0.8247 0.01134 0.00413 -0.0855 0.2439 0.7616
3.500 0.8511 0.01146 0.00426 -0.0850 0.2410 0.7740
3.750 0.8770 0.01158 0.00439 -0.0844 0.2376 0.7858
4.000 0.9024 0.01171 0.00453 -0.0837 0.2341 0.7997
4.250 0.9274 0.01187 0.00469 -0.0830 0.2308 0.8140
4.500 0.9523 0.01200 0.00485 -0.0823 0.2280 0.8295
4.750 0.9770 0.01206 0.00499 -0.0814 0.2260 0.8544
5.000 1.0161 0.01204 0.00515 -0.0837 0.2232 1.0000
5.250 1.0421 0.01224 0.00533 -0.0832 0.2208 1.0000
5.500 1.0677 0.01246 0.00552 -0.0827 0.2184 1.0000
5.750 1.0929 0.01269 0.00573 -0.0822 0.2161 1.0000
6.000 1.1177 0.01295 0.00595 -0.0816 0.2137 1.0000
6.250 1.1430 0.01317 0.00617 -0.0810 0.2119 1.0000
6.500 1.1684 0.01337 0.00638 -0.0805 0.2099 1.0000
6.750 1.1935 0.01358 0.00659 -0.0799 0.2076 1.0000
7.000 1.2182 0.01381 0.00683 -0.0793 0.2055 1.0000
7.250 1.2424 0.01406 0.00708 -0.0786 0.2034 1.0000
7.500 1.2661 0.01433 0.00733 -0.0779 0.2011 1.0000
7.750 1.2891 0.01464 0.00762 -0.0770 0.1988 1.0000
8.000 1.3126 0.01491 0.00791 -0.0762 0.1971 1.0000
8.250 1.3364 0.01515 0.00818 -0.0755 0.1958 1.0000
8.500 1.3598 0.01540 0.00846 -0.0747 0.1944 1.0000
8.750 1.3828 0.01566 0.00875 -0.0739 0.1926 1.0000
9.000 1.4052 0.01594 0.00906 -0.0730 0.1907 1.0000
9.250 1.4271 0.01624 0.00937 -0.0720 0.1891 1.0000
9.500 1.4482 0.01655 0.00970 -0.0708 0.1876 1.0000
9.750 1.4677 0.01688 0.01005 -0.0695 0.1861 1.0000
10.000 1.4860 0.01725 0.01043 -0.0679 0.1845 1.0000
10.250 1.5041 0.01762 0.01083 -0.0663 0.1830 1.0000
10.500 1.5238 0.01793 0.01119 -0.0650 0.1818 1.0000
10.750 1.5431 0.01824 0.01157 -0.0636 0.1805 1.0000
11.000 1.5618 0.01860 0.01198 -0.0622 0.1790 1.0000
11.250 1.5799 0.01897 0.01240 -0.0608 0.1774 1.0000
11.500 1.5973 0.01937 0.01284 -0.0593 0.1755 1.0000
11.750 1.6139 0.01981 0.01332 -0.0578 0.1736 1.0000
12.000 1.6295 0.02031 0.01384 -0.0561 0.1718 1.0000
12.250 1.6433 0.02090 0.01445 -0.0544 0.1696 1.0000
12.500 1.6608 0.02133 0.01497 -0.0531 0.1678 1.0000
12.750 1.6773 0.02181 0.01553 -0.0517 0.1653 1.0000
13.000 1.6923 0.02238 0.01614 -0.0503 0.1623 1.0000
13.250 1.7054 0.02306 0.01686 -0.0487 0.1592 1.0000
13.500 1.7164 0.02388 0.01770 -0.0471 0.1560 1.0000
13.750 1.7314 0.02452 0.01842 -0.0459 0.1525 1.0000
14.000 1.7432 0.02537 0.01931 -0.0445 0.1479 1.0000
14.250 1.7514 0.02648 0.02044 -0.0429 0.1440 1.0000
14.500 1.7632 0.02742 0.02145 -0.0417 0.1398 1.0000
14.750 1.7706 0.02869 0.02275 -0.0403 0.1340 1.0000
15.000 1.7768 0.03013 0.02422 -0.0391 0.1279 1.0000
15.250 1.7790 0.03197 0.02608 -0.0378 0.1205 1.0000
15.500 1.7758 0.03440 0.02850 -0.0367 0.1100 1.0000
15.750 1.7672 0.03749 0.03159 -0.0358 0.1001 1.0000
16.000 1.7583 0.04080 0.03493 -0.0352 0.0940 1.0000
16.250 1.7477 0.04446 0.03866 -0.0350 0.0897 1.0000
16.500 1.7393 0.04808 0.04236 -0.0351 0.0868 1.0000
16.750 1.7260 0.05247 0.04685 -0.0357 0.0842 1.0000
17.000 1.7102 0.05742 0.05191 -0.0366 0.0822 1.0000
17.250 1.6979 0.06214 0.05676 -0.0378 0.0807 1.0000
17.500 1.6827 0.06749 0.06224 -0.0394 0.0792 1.0000
17.750 1.6631 0.07366 0.06854 -0.0414 0.0779 1.0000
18.000 1.6400 0.08056 0.07559 -0.0440 0.0767 1.0000
18.250 1.6140 0.08807 0.08324 -0.0470 0.0757 1.0000
18.500 1.5869 0.09592 0.09122 -0.0502 0.0747 1.0000
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