NACA 4418 (naca4418-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4418 (naca4418-il) Reynolds number: 100,000 Max Cl/Cd: 47.7 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4418-il-100000-n5.txt Download as CSV file: xf-naca4418-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4401 0.10738 0.10128 -0.0617 1.0000 0.0688
-13.000 -0.7459 0.05786 0.05111 -0.0881 1.0000 0.0705
-12.750 -0.7914 0.05352 0.04661 -0.0867 1.0000 0.0705
-12.500 -0.8293 0.05094 0.04392 -0.0828 1.0000 0.0706
-12.250 -0.8630 0.04922 0.04211 -0.0774 0.9996 0.0708
-12.000 -0.8545 0.04677 0.03945 -0.0789 0.9937 0.0723
-11.750 -0.8477 0.04391 0.03623 -0.0800 0.9867 0.0743
-11.500 -0.8292 0.04190 0.03402 -0.0814 0.9815 0.0761
-11.250 -0.8077 0.04076 0.03285 -0.0821 0.9757 0.0778
-11.000 -0.7866 0.03922 0.03114 -0.0830 0.9703 0.0800
-10.750 -0.7682 0.03733 0.02886 -0.0836 0.9647 0.0829
-10.500 -0.7441 0.03653 0.02814 -0.0840 0.9586 0.0848
-10.250 -0.7162 0.03545 0.02694 -0.0853 0.9543 0.0877
-10.000 -0.6972 0.03412 0.02529 -0.0851 0.9474 0.0909
-9.750 -0.6702 0.03338 0.02462 -0.0857 0.9419 0.0934
-9.500 -0.6390 0.03243 0.02355 -0.0873 0.9381 0.0971
-9.250 -0.6196 0.03150 0.02242 -0.0865 0.9303 0.1004
-9.000 -0.5908 0.03082 0.02179 -0.0873 0.9249 0.1036
-8.750 -0.5573 0.02994 0.02073 -0.0890 0.9214 0.1082
-8.500 -0.5371 0.02929 0.02005 -0.0880 0.9132 0.1115
-8.250 -0.5074 0.02865 0.01939 -0.0888 0.9077 0.1157
-8.000 -0.4726 0.02783 0.01841 -0.0905 0.9043 0.1209
-7.750 -0.4505 0.02735 0.01797 -0.0897 0.8964 0.1245
-7.500 -0.4216 0.02674 0.01727 -0.0901 0.8904 0.1295
-7.250 -0.3876 0.02604 0.01655 -0.0914 0.8865 0.1344
-7.000 -0.3635 0.02559 0.01609 -0.0909 0.8790 0.1391
-6.750 -0.3360 0.02504 0.01543 -0.0909 0.8723 0.1445
-6.500 -0.3023 0.02446 0.01489 -0.0920 0.8680 0.1500
-6.250 -0.2771 0.02403 0.01438 -0.0915 0.8605 0.1561
-6.000 -0.2502 0.02357 0.01395 -0.0914 0.8533 0.1618
-5.750 -0.2159 0.02303 0.01333 -0.0925 0.8488 0.1701
-5.500 -0.1921 0.02266 0.01301 -0.0917 0.8404 0.1768
-5.250 -0.1634 0.02225 0.01252 -0.0918 0.8334 0.1861
-5.000 -0.1293 0.02171 0.01202 -0.0928 0.8287 0.1959
-4.750 -0.1070 0.02145 0.01173 -0.0917 0.8191 0.2057
-4.500 -0.0768 0.02103 0.01133 -0.0920 0.8124 0.2169
-4.250 -0.0437 0.02059 0.01091 -0.0929 0.8070 0.2292
-4.000 -0.0216 0.02042 0.01073 -0.0917 0.7965 0.2409
-3.750 0.0111 0.02005 0.01038 -0.0924 0.7904 0.2546
-3.500 0.0358 0.01987 0.01024 -0.0917 0.7811 0.2673
-3.250 0.0654 0.01961 0.00996 -0.0918 0.7731 0.2820
-3.000 0.0959 0.01938 0.00967 -0.0921 0.7659 0.2981
-2.750 0.1206 0.01920 0.00956 -0.0914 0.7560 0.3128
-2.500 0.1533 0.01887 0.00924 -0.0920 0.7494 0.3304
-2.250 0.1762 0.01877 0.00919 -0.0910 0.7388 0.3475
-2.000 0.2065 0.01851 0.00896 -0.0913 0.7312 0.3689
-1.750 0.2314 0.01837 0.00890 -0.0906 0.7216 0.3914
-1.500 0.2593 0.01815 0.00876 -0.0904 0.7130 0.4174
-1.250 0.2862 0.01799 0.00868 -0.0900 0.7044 0.4458
-1.000 0.3120 0.01785 0.00865 -0.0895 0.6951 0.4767
-0.750 0.3407 0.01767 0.00854 -0.0893 0.6873 0.5150
-0.500 0.3643 0.01760 0.00862 -0.0883 0.6774 0.5554
-0.250 0.3937 0.01743 0.00853 -0.0882 0.6701 0.6015
0.000 0.4158 0.01742 0.00868 -0.0868 0.6602 0.6462
0.500 0.4665 0.01734 0.00882 -0.0848 0.6437 0.7450
0.750 0.4925 0.01736 0.00893 -0.0838 0.6352 0.7943
1.000 0.5241 0.01740 0.00899 -0.0838 0.6277 0.8430
1.250 0.5572 0.01756 0.00919 -0.0844 0.6183 0.8896
1.500 0.6011 0.01767 0.00921 -0.0871 0.6109 0.9326
1.750 0.6441 0.01790 0.00942 -0.0902 0.6013 0.9669
2.000 0.6930 0.01804 0.00945 -0.0944 0.5930 0.9894
2.250 0.7290 0.01823 0.00957 -0.0964 0.5846 1.0000
2.500 0.7472 0.01839 0.00966 -0.0947 0.5767 1.0000
2.750 0.7702 0.01853 0.00966 -0.0938 0.5701 1.0000
3.000 0.7859 0.01878 0.00991 -0.0917 0.5618 1.0000
3.250 0.8074 0.01897 0.01001 -0.0905 0.5546 1.0000
3.500 0.8289 0.01920 0.01016 -0.0894 0.5476 1.0000
3.750 0.8477 0.01947 0.01042 -0.0878 0.5398 1.0000
4.000 0.8720 0.01967 0.01052 -0.0871 0.5331 1.0000
4.250 0.8916 0.01997 0.01082 -0.0857 0.5256 1.0000
4.500 0.9123 0.02025 0.01107 -0.0844 0.5181 1.0000
5.000 0.9553 0.02084 0.01161 -0.0822 0.5037 1.0000
5.250 0.9774 0.02111 0.01184 -0.0812 0.4964 1.0000
5.500 0.9998 0.02141 0.01210 -0.0803 0.4893 1.0000
5.750 1.0176 0.02177 0.01249 -0.0786 0.4811 1.0000
6.000 1.0418 0.02202 0.01266 -0.0779 0.4740 1.0000
6.250 1.0578 0.02243 0.01313 -0.0760 0.4656 1.0000
6.500 1.0776 0.02275 0.01344 -0.0747 0.4578 1.0000
6.750 1.0977 0.02310 0.01377 -0.0734 0.4505 1.0000
7.000 1.1134 0.02352 0.01424 -0.0715 0.4423 1.0000
7.250 1.1363 0.02382 0.01447 -0.0707 0.4355 1.0000
7.500 1.1479 0.02432 0.01507 -0.0681 0.4273 1.0000
7.750 1.1643 0.02471 0.01546 -0.0663 0.4198 1.0000
8.000 1.1807 0.02516 0.01593 -0.0645 0.4126 1.0000
8.250 1.1928 0.02571 0.01653 -0.0622 0.4044 1.0000
8.500 1.2124 0.02609 0.01685 -0.0610 0.3974 1.0000
8.750 1.2209 0.02681 0.01769 -0.0583 0.3888 1.0000
9.000 1.2368 0.02730 0.01816 -0.0566 0.3812 1.0000
9.250 1.2468 0.02805 0.01899 -0.0543 0.3727 1.0000
9.500 1.2594 0.02869 0.01965 -0.0524 0.3645 1.0000
9.750 1.2694 0.02950 0.02051 -0.0503 0.3558 1.0000
10.000 1.2791 0.03030 0.02133 -0.0482 0.3469 1.0000
10.250 1.2873 0.03125 0.02233 -0.0460 0.3377 1.0000
10.500 1.2958 0.03219 0.02327 -0.0440 0.3285 1.0000
10.750 1.3018 0.03337 0.02451 -0.0419 0.3190 1.0000
11.000 1.3096 0.03443 0.02556 -0.0401 0.3101 1.0000
11.250 1.3135 0.03587 0.02710 -0.0381 0.3004 1.0000
11.500 1.3205 0.03708 0.02825 -0.0364 0.2917 1.0000
11.750 1.3220 0.03883 0.03012 -0.0346 0.2818 1.0000
12.000 1.3261 0.04039 0.03167 -0.0330 0.2729 1.0000
12.250 1.3270 0.04231 0.03366 -0.0314 0.2631 1.0000
12.500 1.3284 0.04424 0.03561 -0.0300 0.2541 1.0000
12.750 1.3286 0.04636 0.03774 -0.0287 0.2449 1.0000
13.000 1.3281 0.04868 0.04013 -0.0276 0.2359 1.0000
13.250 1.3278 0.05099 0.04242 -0.0266 0.2275 1.0000
13.500 1.3256 0.05370 0.04523 -0.0258 0.2188 1.0000
13.750 1.3248 0.05623 0.04771 -0.0250 0.2110 1.0000
14.000 1.3215 0.05927 0.05087 -0.0246 0.2027 1.0000
14.250 1.3198 0.06206 0.05363 -0.0241 0.1954 1.0000
14.500 1.3159 0.06533 0.05702 -0.0239 0.1877 1.0000
14.750 1.3137 0.06834 0.06001 -0.0237 0.1810 1.0000
15.000 1.3092 0.07185 0.06364 -0.0238 0.1738 1.0000
15.250 1.3064 0.07503 0.06679 -0.0238 0.1676 1.0000
15.500 1.3012 0.07879 0.07068 -0.0241 0.1607 1.0000
15.750 1.2981 0.08214 0.07400 -0.0244 0.1549 1.0000
16.000 1.2923 0.08611 0.07811 -0.0250 0.1485 1.0000
16.250 1.2887 0.08965 0.08165 -0.0254 0.1429 1.0000
16.500 1.2834 0.09363 0.08574 -0.0262 0.1371 1.0000
16.750 1.2791 0.09743 0.08956 -0.0269 0.1318 1.0000
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