NACA 4412 (naca4412-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4412 (naca4412-il) Reynolds number: 500,000 Max Cl/Cd: 101.1 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4412-il-500000-n5.txt Download as CSV file: xf-naca4412-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4412
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9839 0.03650 0.03291 -0.0919 1.0000 0.0171
-13.750 -1.0013 0.03397 0.03026 -0.0893 1.0000 0.0172
-13.500 -0.9998 0.03206 0.02823 -0.0883 0.9993 0.0175
-13.250 -0.9771 0.03034 0.02640 -0.0903 0.9969 0.0179
-13.000 -0.9520 0.02892 0.02485 -0.0921 0.9948 0.0184
-12.750 -0.9270 0.02762 0.02341 -0.0936 0.9925 0.0190
-12.500 -0.9023 0.02637 0.02200 -0.0947 0.9897 0.0197
-12.250 -0.8760 0.02514 0.02058 -0.0960 0.9873 0.0204
-12.000 -0.8484 0.02399 0.01929 -0.0975 0.9855 0.0209
-11.750 -0.8189 0.02311 0.01835 -0.0990 0.9841 0.0215
-11.500 -0.7933 0.02237 0.01752 -0.0994 0.9807 0.0221
-11.250 -0.7652 0.02163 0.01668 -0.1003 0.9782 0.0227
-11.000 -0.7356 0.02088 0.01581 -0.1014 0.9761 0.0235
-10.750 -0.7056 0.02015 0.01492 -0.1025 0.9743 0.0243
-10.500 -0.6754 0.01938 0.01401 -0.1037 0.9727 0.0249
-10.250 -0.6519 0.01864 0.01323 -0.1035 0.9679 0.0255
-10.000 -0.6237 0.01808 0.01261 -0.1040 0.9646 0.0262
-9.750 -0.5941 0.01755 0.01201 -0.1048 0.9620 0.0270
-9.500 -0.5645 0.01701 0.01138 -0.1055 0.9594 0.0278
-9.250 -0.5397 0.01651 0.01078 -0.1051 0.9540 0.0285
-9.000 -0.5118 0.01603 0.01020 -0.1053 0.9498 0.0291
-8.750 -0.4833 0.01538 0.00947 -0.1058 0.9464 0.0299
-8.500 -0.4581 0.01486 0.00892 -0.1055 0.9401 0.0307
-8.250 -0.4308 0.01442 0.00842 -0.1055 0.9340 0.0315
-8.000 -0.4031 0.01402 0.00796 -0.1055 0.9280 0.0323
-7.750 -0.3768 0.01363 0.00750 -0.1052 0.9207 0.0332
-7.500 -0.3489 0.01324 0.00702 -0.1052 0.9151 0.0339
-7.250 -0.3224 0.01289 0.00660 -0.1050 0.9079 0.0345
-7.000 -0.2954 0.01246 0.00611 -0.1049 0.9011 0.0356
-6.750 -0.2684 0.01210 0.00572 -0.1047 0.8941 0.0367
-6.500 -0.2411 0.01179 0.00536 -0.1046 0.8863 0.0377
-6.250 -0.2136 0.01151 0.00502 -0.1044 0.8787 0.0389
-6.000 -0.1861 0.01125 0.00469 -0.1043 0.8703 0.0400
-5.750 -0.1586 0.01100 0.00438 -0.1042 0.8617 0.0413
-5.500 -0.1312 0.01073 0.00408 -0.1040 0.8526 0.0435
-5.250 -0.1036 0.01052 0.00383 -0.1039 0.8431 0.0460
-5.000 -0.0759 0.01033 0.00358 -0.1038 0.8334 0.0485
-4.750 -0.0484 0.01013 0.00335 -0.1036 0.8229 0.0526
-4.500 -0.0207 0.00997 0.00315 -0.1035 0.8124 0.0572
-4.250 0.0069 0.00982 0.00298 -0.1034 0.8017 0.0633
-4.000 0.0345 0.00968 0.00281 -0.1032 0.7901 0.0695
-3.750 0.0622 0.00958 0.00267 -0.1031 0.7787 0.0765
-3.500 0.0897 0.00946 0.00253 -0.1030 0.7673 0.0838
-3.250 0.1173 0.00939 0.00240 -0.1028 0.7554 0.0905
-3.000 0.1449 0.00928 0.00229 -0.1027 0.7433 0.0991
-2.750 0.1725 0.00921 0.00219 -0.1025 0.7315 0.1080
-2.500 0.1999 0.00915 0.00210 -0.1024 0.7195 0.1193
-2.250 0.2274 0.00908 0.00203 -0.1023 0.7072 0.1343
-2.000 0.2548 0.00898 0.00197 -0.1022 0.6953 0.1559
-1.750 0.2822 0.00891 0.00193 -0.1020 0.6832 0.1788
-1.500 0.3095 0.00887 0.00190 -0.1019 0.6708 0.2001
-1.250 0.3369 0.00884 0.00188 -0.1017 0.6584 0.2201
-1.000 0.3644 0.00882 0.00186 -0.1016 0.6458 0.2407
-0.750 0.3918 0.00881 0.00185 -0.1015 0.6335 0.2596
-0.500 0.4190 0.00881 0.00185 -0.1013 0.6215 0.2780
-0.250 0.4462 0.00880 0.00186 -0.1012 0.6092 0.3019
0.000 0.4735 0.00876 0.00188 -0.1011 0.5972 0.3355
0.250 0.5005 0.00871 0.00191 -0.1009 0.5860 0.3776
0.500 0.5270 0.00858 0.00196 -0.1007 0.5749 0.4545
0.750 0.5527 0.00828 0.00205 -0.1004 0.5642 0.5962
1.000 0.5779 0.00809 0.00215 -0.0999 0.5545 0.7003
1.250 0.6014 0.00792 0.00225 -0.0988 0.5446 0.7994
1.500 0.6233 0.00776 0.00235 -0.0970 0.5357 0.9159
1.750 0.6638 0.00785 0.00240 -0.0996 0.5256 0.9935
2.000 0.6924 0.00795 0.00246 -0.0998 0.5162 1.0000
2.250 0.7187 0.00810 0.00254 -0.0995 0.5073 1.0000
2.500 0.7453 0.00823 0.00263 -0.0992 0.4978 1.0000
2.750 0.7718 0.00837 0.00273 -0.0989 0.4891 1.0000
3.000 0.7983 0.00851 0.00283 -0.0986 0.4803 1.0000
3.250 0.8249 0.00865 0.00294 -0.0984 0.4724 1.0000
3.500 0.8514 0.00880 0.00306 -0.0981 0.4641 1.0000
3.750 0.8779 0.00895 0.00318 -0.0978 0.4561 1.0000
4.000 0.9038 0.00913 0.00332 -0.0975 0.4458 1.0000
4.250 0.9298 0.00930 0.00346 -0.0971 0.4336 1.0000
4.500 0.9556 0.00950 0.00361 -0.0967 0.4215 1.0000
4.750 0.9809 0.00971 0.00378 -0.0963 0.4082 1.0000
5.000 1.0059 0.00995 0.00396 -0.0958 0.3931 1.0000
5.250 1.0295 0.01026 0.00416 -0.0951 0.3689 1.0000
5.500 1.0526 0.01062 0.00440 -0.0943 0.3432 1.0000
5.750 1.0762 0.01095 0.00465 -0.0936 0.3227 1.0000
6.000 1.0996 0.01129 0.00491 -0.0929 0.3039 1.0000
6.250 1.1224 0.01167 0.00521 -0.0921 0.2831 1.0000
6.500 1.1441 0.01213 0.00555 -0.0911 0.2586 1.0000
6.750 1.1648 0.01265 0.00594 -0.0900 0.2314 1.0000
7.000 1.1846 0.01323 0.00638 -0.0888 0.2039 1.0000
7.250 1.2037 0.01384 0.00686 -0.0875 0.1771 1.0000
7.500 1.2218 0.01449 0.00736 -0.0860 0.1507 1.0000
7.750 1.2398 0.01512 0.00789 -0.0845 0.1285 1.0000
8.000 1.2575 0.01574 0.00842 -0.0830 0.1118 1.0000
8.250 1.2747 0.01632 0.00894 -0.0814 0.0985 1.0000
8.500 1.2904 0.01690 0.00948 -0.0794 0.0861 1.0000
8.750 1.3058 0.01751 0.01005 -0.0775 0.0751 1.0000
9.000 1.3215 0.01812 0.01063 -0.0757 0.0671 1.0000
9.250 1.3368 0.01875 0.01125 -0.0739 0.0611 1.0000
9.500 1.3520 0.01940 0.01191 -0.0721 0.0563 1.0000
9.750 1.3667 0.02008 0.01260 -0.0703 0.0524 1.0000
10.000 1.3816 0.02075 0.01330 -0.0686 0.0493 1.0000
10.250 1.3949 0.02154 0.01411 -0.0668 0.0464 1.0000
10.500 1.4087 0.02232 0.01492 -0.0651 0.0442 1.0000
10.750 1.4227 0.02309 0.01575 -0.0635 0.0423 1.0000
11.000 1.4353 0.02397 0.01667 -0.0618 0.0405 1.0000
11.250 1.4465 0.02497 0.01771 -0.0601 0.0388 1.0000
11.500 1.4575 0.02602 0.01881 -0.0584 0.0374 1.0000
11.750 1.4699 0.02701 0.01987 -0.0570 0.0362 1.0000
12.000 1.4808 0.02812 0.02104 -0.0555 0.0349 1.0000
12.250 1.4906 0.02935 0.02233 -0.0541 0.0336 1.0000
12.500 1.4987 0.03077 0.02380 -0.0526 0.0323 1.0000
12.750 1.5065 0.03225 0.02534 -0.0513 0.0313 1.0000
13.000 1.5157 0.03366 0.02684 -0.0501 0.0303 1.0000
13.250 1.5238 0.03522 0.02847 -0.0490 0.0293 1.0000
13.500 1.5307 0.03693 0.03024 -0.0480 0.0282 1.0000
13.750 1.5356 0.03885 0.03222 -0.0469 0.0271 1.0000
14.000 1.5398 0.04092 0.03437 -0.0460 0.0262 1.0000
14.250 1.5458 0.04288 0.03642 -0.0453 0.0253 1.0000
14.500 1.5505 0.04501 0.03865 -0.0447 0.0243 1.0000
14.750 1.5539 0.04734 0.04105 -0.0441 0.0234 1.0000
15.000 1.5557 0.04991 0.04369 -0.0437 0.0225 1.0000
15.250 1.5571 0.05261 0.04646 -0.0434 0.0217 1.0000
15.500 1.5593 0.05527 0.04922 -0.0431 0.0208 1.0000
15.750 1.5602 0.05811 0.05216 -0.0430 0.0199 1.0000
16.000 1.5600 0.06117 0.05530 -0.0431 0.0191 1.0000
16.250 1.5581 0.06451 0.05871 -0.0432 0.0184 1.0000
16.500 1.5561 0.06791 0.06221 -0.0435 0.0177 1.0000
16.750 1.5537 0.07141 0.06582 -0.0439 0.0171 1.0000
17.000 1.5503 0.07510 0.06960 -0.0443 0.0165 1.0000
17.250 1.5460 0.07897 0.07356 -0.0450 0.0159 1.0000
17.500 1.5407 0.08304 0.07772 -0.0457 0.0154 1.0000
17.750 1.5340 0.08735 0.08212 -0.0466 0.0150 1.0000
18.000 1.5273 0.09172 0.08659 -0.0476 0.0146 1.0000
18.250 1.5210 0.09608 0.09106 -0.0487 0.0143 1.0000
18.500 1.5142 0.10058 0.09567 -0.0500 0.0139 1.0000
18.750 1.5069 0.10521 0.10042 -0.0514 0.0136 1.0000
19.000 1.4990 0.10997 0.10528 -0.0529 0.0132 1.0000
19.250 1.4906 0.11488 0.11029 -0.0546 0.0129 1.0000
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Polar data table (+)
Polar graphs
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