USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.99 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa40b-il-1000000-n5.txt Download as CSV file: xf-usa40b-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8780 0.05705 0.05418 -0.0713 1.0000 0.0218
-14.500 -0.9192 0.04686 0.04379 -0.0791 1.0000 0.0218
-14.250 -0.9438 0.03955 0.03630 -0.0852 1.0000 0.0218
-14.000 -0.9601 0.03475 0.03136 -0.0886 1.0000 0.0219
-13.750 -0.9867 0.03136 0.02786 -0.0885 1.0000 0.0219
-13.500 -0.9920 0.02915 0.02553 -0.0880 1.0000 0.0219
-13.250 -0.9766 0.02740 0.02365 -0.0892 0.9991 0.0220
-13.000 -0.9519 0.02583 0.02196 -0.0913 0.9973 0.0221
-12.750 -0.9248 0.02448 0.02050 -0.0933 0.9952 0.0222
-12.500 -0.8961 0.02331 0.01922 -0.0951 0.9933 0.0223
-12.250 -0.8712 0.02224 0.01806 -0.0959 0.9907 0.0224
-12.000 -0.8444 0.02127 0.01700 -0.0968 0.9880 0.0225
-11.750 -0.8155 0.02039 0.01604 -0.0979 0.9856 0.0226
-11.500 -0.7849 0.01959 0.01516 -0.0992 0.9835 0.0227
-11.250 -0.7553 0.01884 0.01434 -0.1002 0.9811 0.0227
-11.000 -0.7308 0.01801 0.01343 -0.1002 0.9765 0.0228
-10.750 -0.7027 0.01708 0.01244 -0.1009 0.9731 0.0230
-10.250 -0.6458 0.01573 0.01100 -0.1019 0.9651 0.0234
-10.000 -0.6152 0.01516 0.01039 -0.1027 0.9606 0.0235
-9.750 -0.5805 0.01462 0.00980 -0.1043 0.9574 0.0237
-9.500 -0.5484 0.01413 0.00928 -0.1052 0.9515 0.0239
-9.250 -0.5117 0.01364 0.00874 -0.1071 0.9439 0.0241
-9.000 -0.4730 0.01315 0.00819 -0.1093 0.9296 0.0243
-8.750 -0.4376 0.01277 0.00769 -0.1108 0.9045 0.0245
-8.500 -0.4104 0.01251 0.00727 -0.1105 0.8716 0.0247
-8.250 -0.3866 0.01233 0.00691 -0.1094 0.8251 0.0250
-8.000 -0.3647 0.01225 0.00658 -0.1080 0.7698 0.0252
-7.750 -0.3405 0.01208 0.00626 -0.1071 0.7409 0.0254
-7.500 -0.3150 0.01188 0.00595 -0.1064 0.7233 0.0256
-7.250 -0.2889 0.01166 0.00565 -0.1059 0.7088 0.0258
-7.000 -0.2624 0.01144 0.00536 -0.1055 0.6968 0.0260
-6.750 -0.2359 0.01125 0.00509 -0.1050 0.6848 0.0262
-6.500 -0.2089 0.01106 0.00484 -0.1046 0.6723 0.0263
-6.250 -0.1825 0.01079 0.00450 -0.1041 0.6598 0.0266
-6.000 -0.1559 0.01057 0.00422 -0.1037 0.6453 0.0270
-5.750 -0.1292 0.01040 0.00398 -0.1032 0.6294 0.0273
-5.500 -0.1023 0.01025 0.00376 -0.1028 0.6112 0.0276
-5.250 -0.0756 0.01014 0.00357 -0.1023 0.5912 0.0280
-5.000 -0.0487 0.01005 0.00339 -0.1018 0.5700 0.0284
-4.750 -0.0222 0.00999 0.00322 -0.1013 0.5429 0.0288
-4.500 0.0040 0.00998 0.00308 -0.1007 0.5107 0.0293
-4.250 0.0301 0.01001 0.00296 -0.1001 0.4749 0.0297
-4.000 0.0565 0.01004 0.00285 -0.0996 0.4450 0.0301
-3.750 0.0833 0.01001 0.00273 -0.0992 0.4222 0.0308
-3.500 0.1102 0.00998 0.00262 -0.0987 0.4028 0.0317
-3.250 0.1373 0.00997 0.00254 -0.0983 0.3849 0.0327
-3.000 0.1645 0.00996 0.00246 -0.0979 0.3685 0.0337
-2.750 0.1918 0.00996 0.00239 -0.0976 0.3539 0.0349
-2.500 0.2194 0.00992 0.00232 -0.0972 0.3432 0.0369
-2.000 0.2745 0.00985 0.00221 -0.0966 0.3255 0.0449
-1.750 0.3018 0.00983 0.00218 -0.0962 0.3164 0.0533
-1.500 0.3295 0.00980 0.00216 -0.0959 0.3091 0.0622
-1.250 0.3570 0.00980 0.00214 -0.0956 0.3012 0.0696
-1.000 0.3846 0.00979 0.00213 -0.0953 0.2950 0.0770
-0.750 0.4124 0.00977 0.00211 -0.0950 0.2896 0.0852
-0.500 0.4398 0.00975 0.00210 -0.0947 0.2837 0.0979
-0.250 0.4670 0.00966 0.00210 -0.0944 0.2782 0.1360
0.000 0.4944 0.00959 0.00213 -0.0941 0.2735 0.1753
0.250 0.5218 0.00958 0.00216 -0.0938 0.2679 0.1978
0.500 0.5490 0.00961 0.00220 -0.0935 0.2616 0.2189
0.750 0.5765 0.00957 0.00223 -0.0932 0.2578 0.2465
1.000 0.6037 0.00953 0.00227 -0.0929 0.2535 0.2858
1.250 0.6305 0.00944 0.00234 -0.0926 0.2490 0.3571
1.500 0.6573 0.00941 0.00242 -0.0922 0.2446 0.4091
1.750 0.6846 0.00940 0.00248 -0.0919 0.2419 0.4449
2.000 0.7116 0.00937 0.00256 -0.0916 0.2385 0.4923
2.250 0.7381 0.00934 0.00266 -0.0912 0.2347 0.5574
2.500 0.7646 0.00937 0.00278 -0.0907 0.2307 0.6062
2.750 0.7913 0.00941 0.00290 -0.0902 0.2275 0.6442
3.000 0.8181 0.00947 0.00301 -0.0898 0.2249 0.6754
3.250 0.8449 0.00956 0.00313 -0.0894 0.2219 0.6958
3.500 0.8716 0.00966 0.00324 -0.0889 0.2191 0.7098
3.750 0.8982 0.00979 0.00337 -0.0885 0.2161 0.7221
4.000 0.9247 0.00993 0.00350 -0.0880 0.2130 0.7334
4.250 0.9514 0.01002 0.00362 -0.0876 0.2116 0.7439
4.500 0.9782 0.01013 0.00374 -0.0872 0.2099 0.7545
4.750 1.0045 0.01024 0.00387 -0.0867 0.2079 0.7651
5.000 1.0306 0.01036 0.00401 -0.0862 0.2058 0.7778
5.250 1.0564 0.01050 0.00416 -0.0857 0.2027 0.7907
5.500 1.0817 0.01064 0.00432 -0.0850 0.1997 0.8056
5.750 1.1068 0.01077 0.00448 -0.0844 0.1975 0.8217
6.000 1.1319 0.01083 0.00462 -0.0837 0.1962 0.8441
6.250 1.1585 0.01075 0.00476 -0.0833 0.1943 0.9198
6.500 1.1942 0.01091 0.00495 -0.0850 0.1920 1.0000
6.750 1.2199 0.01110 0.00511 -0.0845 0.1898 1.0000
7.000 1.2453 0.01129 0.00529 -0.0839 0.1880 1.0000
7.250 1.2704 0.01150 0.00549 -0.0834 0.1861 1.0000
7.500 1.2952 0.01171 0.00570 -0.0828 0.1840 1.0000
7.750 1.3202 0.01191 0.00590 -0.0822 0.1828 1.0000
8.000 1.3453 0.01208 0.00609 -0.0816 0.1817 1.0000
8.250 1.3702 0.01226 0.00629 -0.0811 0.1802 1.0000
8.500 1.3947 0.01246 0.00650 -0.0804 0.1787 1.0000
8.750 1.4189 0.01267 0.00672 -0.0797 0.1771 1.0000
9.000 1.4426 0.01290 0.00694 -0.0790 0.1752 1.0000
9.250 1.4659 0.01314 0.00719 -0.0782 0.1733 1.0000
9.500 1.4888 0.01339 0.00745 -0.0773 0.1716 1.0000
9.750 1.5110 0.01367 0.00773 -0.0764 0.1697 1.0000
10.000 1.5339 0.01389 0.00798 -0.0755 0.1688 1.0000
10.250 1.5565 0.01411 0.00824 -0.0746 0.1679 1.0000
10.500 1.5785 0.01434 0.00850 -0.0736 0.1667 1.0000
10.750 1.5992 0.01458 0.00877 -0.0724 0.1651 1.0000
11.000 1.6186 0.01485 0.00905 -0.0710 0.1624 1.0000
11.250 1.6369 0.01517 0.00936 -0.0694 0.1595 1.0000
11.500 1.6540 0.01553 0.00973 -0.0676 0.1562 1.0000
11.750 1.6733 0.01580 0.01004 -0.0662 0.1545 1.0000
12.000 1.6916 0.01611 0.01038 -0.0648 0.1517 1.0000
12.250 1.7090 0.01648 0.01075 -0.0632 0.1485 1.0000
12.500 1.7239 0.01697 0.01123 -0.0613 0.1434 1.0000
12.750 1.7404 0.01739 0.01167 -0.0597 0.1385 1.0000
13.000 1.7530 0.01801 0.01226 -0.0577 0.1318 1.0000
13.250 1.7650 0.01868 0.01290 -0.0557 0.1233 1.0000
13.500 1.7715 0.01967 0.01383 -0.0531 0.1112 1.0000
13.750 1.7720 0.02104 0.01512 -0.0500 0.0970 1.0000
14.000 1.7749 0.02234 0.01640 -0.0474 0.0895 1.0000
14.250 1.7801 0.02356 0.01763 -0.0453 0.0851 1.0000
14.500 1.7858 0.02481 0.01891 -0.0434 0.0818 1.0000
14.750 1.7929 0.02603 0.02018 -0.0418 0.0791 1.0000
15.000 1.7975 0.02749 0.02168 -0.0402 0.0765 1.0000
15.250 1.7998 0.02923 0.02346 -0.0387 0.0738 1.0000
15.500 1.8061 0.03075 0.02504 -0.0376 0.0723 1.0000
15.750 1.8102 0.03252 0.02688 -0.0367 0.0698 1.0000
16.000 1.8099 0.03480 0.02921 -0.0358 0.0670 1.0000
16.250 1.8088 0.03726 0.03173 -0.0352 0.0650 1.0000
16.500 1.8101 0.03958 0.03413 -0.0348 0.0628 1.0000
16.750 1.8056 0.04260 0.03721 -0.0345 0.0598 1.0000
17.000 1.7966 0.04623 0.04090 -0.0345 0.0566 1.0000
17.250 1.7852 0.05032 0.04507 -0.0349 0.0527 1.0000
17.500 1.7649 0.05574 0.05056 -0.0359 0.0483 1.0000
18.000 1.7167 0.06855 0.06360 -0.0395 0.0425 1.0000
18.250 1.6854 0.07646 0.07163 -0.0422 0.0405 1.0000
18.500 1.6560 0.08437 0.07970 -0.0452 0.0396 1.0000
18.750 1.6267 0.09241 0.08790 -0.0484 0.0392 1.0000
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