NACA 4418 (naca4418-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4418 (naca4418-il) Reynolds number: 500,000 Max Cl/Cd: 87.96 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4418-il-500000-n5.txt Download as CSV file: xf-naca4418-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.8703 0.08862 0.08433 -0.0792 1.0000 0.0339
-18.000 -0.8851 0.08315 0.07881 -0.0820 1.0000 0.0341
-17.750 -0.9026 0.07746 0.07304 -0.0850 1.0000 0.0343
-17.500 -0.9230 0.07164 0.06713 -0.0880 1.0000 0.0345
-17.250 -0.9452 0.06578 0.06118 -0.0909 1.0000 0.0346
-17.000 -0.9685 0.05984 0.05514 -0.0937 1.0000 0.0348
-16.750 -0.9912 0.05414 0.04932 -0.0963 1.0000 0.0349
-16.500 -1.0126 0.04878 0.04385 -0.0986 1.0000 0.0350
-16.250 -1.0323 0.04398 0.03894 -0.1002 1.0000 0.0352
-16.000 -1.0511 0.03989 0.03474 -0.1009 1.0000 0.0353
-15.750 -1.0703 0.03654 0.03129 -0.1004 1.0000 0.0355
-15.500 -1.0623 0.03340 0.02804 -0.1038 0.9974 0.0358
-15.250 -1.0493 0.03088 0.02541 -0.1068 0.9945 0.0363
-15.000 -1.0336 0.02889 0.02330 -0.1092 0.9920 0.0367
-14.750 -1.0192 0.02729 0.02160 -0.1103 0.9878 0.0372
-14.500 -1.0017 0.02588 0.02012 -0.1115 0.9843 0.0377
-14.250 -0.9819 0.02456 0.01873 -0.1128 0.9816 0.0384
-14.000 -0.9656 0.02355 0.01767 -0.1126 0.9768 0.0390
-13.750 -0.9475 0.02268 0.01675 -0.1122 0.9719 0.0398
-13.500 -0.9244 0.02188 0.01589 -0.1126 0.9687 0.0407
-13.250 -0.9041 0.02121 0.01514 -0.1121 0.9641 0.0415
-13.000 -0.8848 0.02051 0.01441 -0.1114 0.9585 0.0424
-12.750 -0.8617 0.01983 0.01369 -0.1113 0.9546 0.0434
-12.500 -0.8398 0.01925 0.01307 -0.1108 0.9498 0.0446
-12.250 -0.8191 0.01875 0.01251 -0.1099 0.9437 0.0458
-12.000 -0.7952 0.01819 0.01192 -0.1096 0.9391 0.0471
-11.750 -0.7725 0.01770 0.01140 -0.1091 0.9338 0.0487
-11.500 -0.7502 0.01727 0.01093 -0.1083 0.9272 0.0505
-11.250 -0.7254 0.01682 0.01044 -0.1080 0.9220 0.0524
-11.000 -0.7019 0.01642 0.01002 -0.1074 0.9156 0.0546
-10.750 -0.6777 0.01606 0.00961 -0.1068 0.9087 0.0568
-10.500 -0.6521 0.01567 0.00919 -0.1066 0.9027 0.0591
-10.250 -0.6279 0.01537 0.00885 -0.1059 0.8951 0.0615
-10.000 -0.6025 0.01504 0.00848 -0.1056 0.8879 0.0636
-9.750 -0.5768 0.01474 0.00815 -0.1052 0.8812 0.0660
-9.500 -0.5510 0.01448 0.00784 -0.1048 0.8734 0.0683
-9.250 -0.5249 0.01418 0.00750 -0.1045 0.8664 0.0705
-9.000 -0.4991 0.01393 0.00723 -0.1041 0.8586 0.0730
-8.750 -0.4725 0.01373 0.00695 -0.1038 0.8507 0.0753
-8.500 -0.4465 0.01346 0.00666 -0.1035 0.8431 0.0776
-8.250 -0.4202 0.01323 0.00640 -0.1032 0.8346 0.0800
-8.000 -0.3932 0.01305 0.00614 -0.1029 0.8269 0.0822
-7.750 -0.3670 0.01282 0.00589 -0.1026 0.8183 0.0844
-7.500 -0.3404 0.01262 0.00565 -0.1023 0.8097 0.0869
-7.250 -0.3135 0.01244 0.00544 -0.1021 0.8015 0.0895
-7.000 -0.2868 0.01227 0.00521 -0.1018 0.7924 0.0920
-6.750 -0.2602 0.01208 0.00500 -0.1015 0.7839 0.0949
-6.500 -0.2333 0.01192 0.00481 -0.1012 0.7746 0.0982
-6.250 -0.2065 0.01176 0.00461 -0.1009 0.7659 0.1021
-6.000 -0.1798 0.01159 0.00443 -0.1007 0.7562 0.1067
-5.750 -0.1529 0.01147 0.00425 -0.1004 0.7472 0.1105
-5.500 -0.1261 0.01130 0.00408 -0.1001 0.7375 0.1152
-5.250 -0.0993 0.01119 0.00392 -0.0998 0.7279 0.1201
-5.000 -0.0725 0.01104 0.00378 -0.0995 0.7179 0.1262
-4.750 -0.0458 0.01093 0.00364 -0.0992 0.7084 0.1334
-4.500 -0.0188 0.01081 0.00353 -0.0989 0.6983 0.1428
-4.250 0.0077 0.01072 0.00343 -0.0986 0.6882 0.1528
-4.000 0.0349 0.01062 0.00334 -0.0984 0.6782 0.1630
-3.750 0.0617 0.01058 0.00326 -0.0980 0.6684 0.1729
-3.500 0.0887 0.01050 0.00319 -0.0978 0.6580 0.1827
-3.250 0.1155 0.01047 0.00312 -0.0975 0.6481 0.1902
-3.000 0.1427 0.01041 0.00306 -0.0972 0.6383 0.1985
-2.750 0.1694 0.01041 0.00301 -0.0969 0.6287 0.2058
-2.500 0.1964 0.01035 0.00296 -0.0967 0.6187 0.2148
-2.250 0.2230 0.01035 0.00292 -0.0963 0.6093 0.2228
-2.000 0.2501 0.01029 0.00289 -0.0961 0.6003 0.2332
-1.500 0.3036 0.01026 0.00287 -0.0955 0.5823 0.2599
-1.250 0.3301 0.01026 0.00288 -0.0952 0.5735 0.2752
-1.000 0.3570 0.01025 0.00288 -0.0949 0.5657 0.2897
-0.750 0.3838 0.01025 0.00289 -0.0946 0.5571 0.3030
-0.500 0.4102 0.01028 0.00291 -0.0943 0.5494 0.3183
-0.250 0.4372 0.01024 0.00294 -0.0940 0.5419 0.3385
0.000 0.4632 0.01023 0.00297 -0.0937 0.5341 0.3597
0.250 0.4898 0.01022 0.00300 -0.0934 0.5271 0.3800
0.500 0.5163 0.01020 0.00304 -0.0931 0.5198 0.4024
0.750 0.5421 0.01022 0.00310 -0.0926 0.5128 0.4286
1.000 0.5686 0.01018 0.00316 -0.0924 0.5062 0.4618
1.250 0.5945 0.01015 0.00324 -0.0920 0.4993 0.5022
1.500 0.6196 0.01016 0.00333 -0.0914 0.4927 0.5429
1.750 0.6461 0.01013 0.00342 -0.0911 0.4864 0.5798
2.000 0.6718 0.01014 0.00351 -0.0907 0.4797 0.6134
2.250 0.6965 0.01019 0.00362 -0.0900 0.4733 0.6478
2.500 0.7224 0.01018 0.00374 -0.0896 0.4673 0.6852
2.750 0.7470 0.01017 0.00387 -0.0888 0.4606 0.7306
3.000 0.7703 0.01022 0.00401 -0.0878 0.4543 0.7749
3.250 0.7940 0.01020 0.00416 -0.0868 0.4482 0.8261
3.500 0.8155 0.01023 0.00434 -0.0852 0.4414 0.8818
3.750 0.8391 0.01039 0.00452 -0.0841 0.4341 0.9263
4.000 0.8704 0.01054 0.00468 -0.0848 0.4255 0.9568
4.500 0.9406 0.01096 0.00502 -0.0882 0.4090 0.9968
4.750 0.9638 0.01114 0.00517 -0.0873 0.4020 1.0000
5.000 0.9833 0.01132 0.00531 -0.0857 0.3960 1.0000
5.250 1.0038 0.01148 0.00546 -0.0843 0.3892 1.0000
5.500 1.0226 0.01169 0.00563 -0.0826 0.3823 1.0000
5.750 1.0431 0.01189 0.00582 -0.0812 0.3763 1.0000
6.000 1.0643 0.01210 0.00601 -0.0800 0.3691 1.0000
6.250 1.0834 0.01239 0.00626 -0.0785 0.3619 1.0000
6.500 1.1055 0.01260 0.00648 -0.0776 0.3553 1.0000
6.750 1.1259 0.01289 0.00674 -0.0763 0.3476 1.0000
7.000 1.1461 0.01319 0.00702 -0.0751 0.3403 1.0000
7.250 1.1666 0.01350 0.00731 -0.0740 0.3320 1.0000
7.500 1.1854 0.01388 0.00765 -0.0726 0.3226 1.0000
7.750 1.2036 0.01430 0.00803 -0.0711 0.3115 1.0000
8.000 1.2226 0.01470 0.00840 -0.0699 0.3016 1.0000
8.250 1.2392 0.01521 0.00886 -0.0683 0.2917 1.0000
8.500 1.2579 0.01565 0.00929 -0.0670 0.2812 1.0000
8.750 1.2737 0.01624 0.00982 -0.0654 0.2691 1.0000
9.000 1.2876 0.01694 0.01044 -0.0636 0.2541 1.0000
9.250 1.3003 0.01771 0.01114 -0.0617 0.2387 1.0000
9.500 1.3133 0.01851 0.01187 -0.0600 0.2253 1.0000
9.750 1.3274 0.01927 0.01259 -0.0584 0.2143 1.0000
10.000 1.3416 0.02004 0.01334 -0.0569 0.2052 1.0000
10.250 1.3539 0.02094 0.01421 -0.0553 0.1962 1.0000
10.500 1.3678 0.02178 0.01504 -0.0539 0.1877 1.0000
10.750 1.3793 0.02277 0.01601 -0.0523 0.1796 1.0000
11.000 1.3909 0.02380 0.01702 -0.0508 0.1713 1.0000
11.250 1.4022 0.02488 0.01809 -0.0494 0.1640 1.0000
11.500 1.4121 0.02607 0.01928 -0.0479 0.1566 1.0000
11.750 1.4228 0.02724 0.02045 -0.0466 0.1503 1.0000
12.000 1.4317 0.02857 0.02178 -0.0452 0.1435 1.0000
12.250 1.4412 0.02990 0.02313 -0.0440 0.1375 1.0000
12.500 1.4484 0.03145 0.02467 -0.0427 0.1309 1.0000
12.750 1.4569 0.03294 0.02617 -0.0416 0.1246 1.0000
13.000 1.4621 0.03474 0.02797 -0.0404 0.1183 1.0000
13.250 1.4683 0.03652 0.02977 -0.0393 0.1117 1.0000
13.500 1.4726 0.03851 0.03177 -0.0383 0.1056 1.0000
13.750 1.4757 0.04066 0.03392 -0.0373 0.0995 1.0000
14.000 1.4792 0.04283 0.03611 -0.0365 0.0942 1.0000
14.250 1.4806 0.04527 0.03856 -0.0357 0.0893 1.0000
14.500 1.4834 0.04763 0.04096 -0.0350 0.0849 1.0000
14.750 1.4841 0.05023 0.04359 -0.0344 0.0811 1.0000
15.000 1.4860 0.05276 0.04616 -0.0339 0.0775 1.0000
15.250 1.4850 0.05566 0.04910 -0.0335 0.0742 1.0000
15.500 1.4863 0.05837 0.05186 -0.0332 0.0712 1.0000
15.750 1.4852 0.06137 0.05491 -0.0330 0.0683 1.0000
16.000 1.4845 0.06435 0.05795 -0.0328 0.0658 1.0000
16.250 1.4834 0.06744 0.06109 -0.0328 0.0633 1.0000
16.500 1.4799 0.07086 0.06455 -0.0328 0.0611 1.0000
16.750 1.4789 0.07401 0.06777 -0.0329 0.0591 1.0000
17.000 1.4764 0.07736 0.07118 -0.0331 0.0570 1.0000
17.250 1.4716 0.08105 0.07492 -0.0334 0.0553 1.0000
17.500 1.4690 0.08449 0.07843 -0.0337 0.0537 1.0000
17.750 1.4663 0.08798 0.08199 -0.0341 0.0522 1.0000
18.000 1.4620 0.09171 0.08578 -0.0347 0.0509 1.0000
18.250 1.4570 0.09553 0.08966 -0.0353 0.0497 1.0000
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