NACA 4418 (naca4418-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4418 (naca4418-il) Reynolds number: 200,000 Max Cl/Cd: 65.39 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4418-il-200000-n5.txt Download as CSV file: xf-naca4418-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4418
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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.6940 0.09304 0.08793 -0.0770 1.0000 0.0478
-16.250 -0.7556 0.07986 0.07449 -0.0846 1.0000 0.0482
-16.000 -0.7876 0.07227 0.06675 -0.0886 1.0000 0.0485
-15.750 -0.8128 0.06600 0.06034 -0.0918 1.0000 0.0488
-15.500 -0.8346 0.06053 0.05474 -0.0942 1.0000 0.0492
-15.250 -0.8541 0.05570 0.04979 -0.0960 1.0000 0.0496
-15.000 -0.8719 0.05149 0.04546 -0.0972 1.0000 0.0500
-14.750 -0.8893 0.04782 0.04167 -0.0975 1.0000 0.0503
-14.500 -0.9069 0.04467 0.03840 -0.0970 1.0000 0.0507
-14.250 -0.9254 0.04199 0.03560 -0.0956 1.0000 0.0511
-14.000 -0.9447 0.03981 0.03334 -0.0931 1.0000 0.0514
-13.750 -0.9402 0.03764 0.03112 -0.0942 0.9970 0.0519
-13.500 -0.9257 0.03571 0.02909 -0.0964 0.9930 0.0527
-13.250 -0.9131 0.03410 0.02739 -0.0973 0.9877 0.0537
-13.000 -0.8975 0.03269 0.02585 -0.0981 0.9829 0.0550
-12.750 -0.8810 0.03141 0.02441 -0.0984 0.9779 0.0564
-12.500 -0.8623 0.03031 0.02328 -0.0987 0.9723 0.0575
-12.250 -0.8366 0.02929 0.02220 -0.0999 0.9688 0.0591
-12.000 -0.8154 0.02836 0.02117 -0.1001 0.9638 0.0608
-11.750 -0.7936 0.02744 0.02014 -0.1001 0.9585 0.0626
-11.500 -0.7657 0.02661 0.01928 -0.1013 0.9552 0.0643
-11.250 -0.7351 0.02580 0.01839 -0.1028 0.9530 0.0665
-11.000 -0.7172 0.02516 0.01763 -0.1015 0.9454 0.0687
-10.750 -0.6903 0.02448 0.01695 -0.1021 0.9412 0.0708
-10.500 -0.6599 0.02381 0.01620 -0.1032 0.9382 0.0736
-10.250 -0.6384 0.02325 0.01555 -0.1025 0.9317 0.0759
-10.000 -0.6133 0.02268 0.01497 -0.1024 0.9261 0.0782
-9.750 -0.5833 0.02209 0.01429 -0.1032 0.9223 0.0811
-9.500 -0.5581 0.02155 0.01369 -0.1030 0.9167 0.0837
-9.250 -0.5348 0.02108 0.01321 -0.1024 0.9097 0.0863
-9.000 -0.5051 0.02057 0.01261 -0.1029 0.9052 0.0895
-8.750 -0.4789 0.02007 0.01208 -0.1028 0.8995 0.0923
-8.500 -0.4555 0.01966 0.01165 -0.1021 0.8920 0.0951
-8.250 -0.4261 0.01921 0.01111 -0.1025 0.8870 0.0985
-8.000 -0.4001 0.01876 0.01065 -0.1022 0.8807 0.1016
-7.750 -0.3755 0.01839 0.01027 -0.1017 0.8730 0.1051
-7.500 -0.3454 0.01799 0.00978 -0.1021 0.8677 0.1093
-7.250 -0.3210 0.01759 0.00941 -0.1015 0.8601 0.1131
-7.000 -0.2944 0.01725 0.00903 -0.1013 0.8526 0.1174
-6.750 -0.2643 0.01684 0.00857 -0.1017 0.8470 0.1218
-6.500 -0.2409 0.01655 0.00830 -0.1009 0.8378 0.1261
-6.250 -0.2122 0.01623 0.00791 -0.1009 0.8306 0.1313
-6.000 -0.1859 0.01592 0.00762 -0.1006 0.8227 0.1365
-5.750 -0.1591 0.01566 0.00733 -0.1003 0.8142 0.1429
-5.500 -0.1305 0.01537 0.00703 -0.1004 0.8070 0.1499
-5.250 -0.1050 0.01518 0.00682 -0.0998 0.7974 0.1578
-5.000 -0.0766 0.01493 0.00657 -0.0998 0.7895 0.1670
-4.750 -0.0507 0.01476 0.00639 -0.0994 0.7800 0.1762
-4.500 -0.0227 0.01459 0.00616 -0.0993 0.7713 0.1864
-4.250 0.0036 0.01440 0.00599 -0.0989 0.7621 0.1961
-4.000 0.0310 0.01426 0.00580 -0.0986 0.7527 0.2061
-3.750 0.0577 0.01410 0.00564 -0.0983 0.7434 0.2165
-3.500 0.0845 0.01396 0.00549 -0.0980 0.7337 0.2267
-3.250 0.1115 0.01385 0.00536 -0.0977 0.7245 0.2381
-3.000 0.1380 0.01373 0.00526 -0.0974 0.7145 0.2502
-2.750 0.1650 0.01365 0.00516 -0.0971 0.7051 0.2631
-2.500 0.1917 0.01359 0.00509 -0.0967 0.6951 0.2772
-2.250 0.2185 0.01351 0.00501 -0.0964 0.6858 0.2915
-2.000 0.2448 0.01345 0.00495 -0.0960 0.6756 0.3058
-1.750 0.2716 0.01341 0.00488 -0.0957 0.6664 0.3212
-1.500 0.2976 0.01334 0.00484 -0.0953 0.6566 0.3380
-1.250 0.3239 0.01327 0.00480 -0.0949 0.6476 0.3582
-1.000 0.3495 0.01319 0.00479 -0.0944 0.6378 0.3819
-0.500 0.4009 0.01306 0.00479 -0.0934 0.6199 0.4353
-0.250 0.4266 0.01301 0.00480 -0.0929 0.6113 0.4675
0.000 0.4517 0.01295 0.00486 -0.0923 0.6026 0.5042
0.250 0.4768 0.01291 0.00492 -0.0916 0.5942 0.5460
0.500 0.5018 0.01287 0.00499 -0.0909 0.5862 0.5882
0.750 0.5265 0.01285 0.00508 -0.0902 0.5778 0.6289
1.000 0.5512 0.01286 0.00516 -0.0893 0.5705 0.6696
1.250 0.5752 0.01284 0.00529 -0.0884 0.5625 0.7130
1.500 0.5991 0.01286 0.00541 -0.0872 0.5548 0.7586
1.750 0.6232 0.01291 0.00555 -0.0861 0.5478 0.8037
2.000 0.6486 0.01299 0.00572 -0.0852 0.5401 0.8493
2.250 0.6787 0.01314 0.00588 -0.0853 0.5329 0.8939
2.500 0.7142 0.01330 0.00607 -0.0867 0.5254 0.9345
2.750 0.7517 0.01350 0.00623 -0.0886 0.5175 0.9644
3.000 0.7915 0.01372 0.00637 -0.0912 0.5103 0.9833
3.250 0.8312 0.01391 0.00655 -0.0938 0.5023 0.9971
3.500 0.8556 0.01409 0.00666 -0.0933 0.4955 1.0000
3.750 0.8750 0.01426 0.00678 -0.0917 0.4890 1.0000
4.000 0.8945 0.01442 0.00693 -0.0901 0.4821 1.0000
4.250 0.9145 0.01462 0.00706 -0.0886 0.4754 1.0000
4.500 0.9350 0.01481 0.00723 -0.0873 0.4686 1.0000
4.750 0.9552 0.01501 0.00741 -0.0859 0.4610 1.0000
5.250 0.9957 0.01545 0.00779 -0.0831 0.4459 1.0000
5.500 1.0157 0.01570 0.00800 -0.0817 0.4384 1.0000
5.750 1.0361 0.01594 0.00823 -0.0803 0.4315 1.0000
6.000 1.0561 0.01619 0.00848 -0.0790 0.4241 1.0000
6.250 1.0751 0.01647 0.00871 -0.0774 0.4174 1.0000
6.500 1.0940 0.01673 0.00899 -0.0758 0.4104 1.0000
6.750 1.1119 0.01702 0.00928 -0.0741 0.4032 1.0000
7.000 1.1298 0.01736 0.00958 -0.0725 0.3965 1.0000
7.250 1.1482 0.01767 0.00993 -0.0709 0.3890 1.0000
7.500 1.1654 0.01805 0.01028 -0.0692 0.3817 1.0000
7.750 1.1834 0.01842 0.01067 -0.0677 0.3743 1.0000
8.000 1.2004 0.01883 0.01109 -0.0661 0.3665 1.0000
8.250 1.2168 0.01928 0.01153 -0.0644 0.3590 1.0000
8.500 1.2331 0.01974 0.01202 -0.0628 0.3503 1.0000
8.750 1.2475 0.02029 0.01255 -0.0609 0.3417 1.0000
9.000 1.2621 0.02085 0.01312 -0.0592 0.3317 1.0000
9.250 1.2755 0.02149 0.01375 -0.0573 0.3224 1.0000
9.500 1.2885 0.02217 0.01443 -0.0555 0.3125 1.0000
9.750 1.3016 0.02289 0.01516 -0.0538 0.3032 1.0000
10.000 1.3124 0.02374 0.01599 -0.0518 0.2933 1.0000
10.250 1.3243 0.02458 0.01685 -0.0501 0.2828 1.0000
10.500 1.3330 0.02562 0.01786 -0.0482 0.2719 1.0000
10.750 1.3406 0.02677 0.01899 -0.0463 0.2602 1.0000
11.000 1.3491 0.02794 0.02015 -0.0445 0.2486 1.0000
11.250 1.3558 0.02926 0.02146 -0.0428 0.2379 1.0000
11.500 1.3613 0.03072 0.02290 -0.0410 0.2276 1.0000
11.750 1.3689 0.03211 0.02431 -0.0396 0.2180 1.0000
12.000 1.3734 0.03375 0.02594 -0.0380 0.2094 1.0000
12.250 1.3793 0.03536 0.02757 -0.0367 0.2006 1.0000
12.500 1.3839 0.03713 0.02936 -0.0354 0.1928 1.0000
12.750 1.3879 0.03902 0.03127 -0.0342 0.1849 1.0000
13.000 1.3918 0.04098 0.03325 -0.0331 0.1779 1.0000
13.250 1.3945 0.04312 0.03541 -0.0321 0.1707 1.0000
13.500 1.3975 0.04529 0.03761 -0.0313 0.1642 1.0000
13.750 1.3994 0.04763 0.03999 -0.0305 0.1575 1.0000
14.000 1.4010 0.05005 0.04245 -0.0298 0.1513 1.0000
14.250 1.4018 0.05263 0.04507 -0.0293 0.1448 1.0000
14.500 1.4022 0.05531 0.04779 -0.0288 0.1389 1.0000
14.750 1.4017 0.05815 0.05067 -0.0285 0.1326 1.0000
15.000 1.4010 0.06105 0.05361 -0.0282 0.1270 1.0000
15.250 1.3992 0.06414 0.05675 -0.0281 0.1211 1.0000
15.500 1.3973 0.06730 0.05996 -0.0280 0.1159 1.0000
15.750 1.3945 0.07063 0.06333 -0.0281 0.1107 1.0000
16.000 1.3915 0.07402 0.06677 -0.0282 0.1061 1.0000
16.250 1.3882 0.07749 0.07029 -0.0285 0.1014 1.0000
16.500 1.3835 0.08118 0.07403 -0.0288 0.0973 1.0000
16.750 1.3800 0.08478 0.07770 -0.0293 0.0932 1.0000
17.000 1.3737 0.08877 0.08171 -0.0298 0.0898 1.0000
17.250 1.3712 0.09230 0.08532 -0.0304 0.0861 1.0000
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