NACA 4418 (naca4418-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4418 (naca4418-il) Reynolds number: 200,000 Max Cl/Cd: 67.02 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4418-il-200000.txt Download as CSV file: xf-naca4418-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7566 0.06480 0.05984 -0.0954 1.0000 0.0682
-14.250 -0.8095 0.05804 0.05289 -0.0973 1.0000 0.0680
-14.000 -0.8537 0.05371 0.04840 -0.0962 1.0000 0.0679
-13.750 -0.8942 0.05079 0.04535 -0.0928 1.0000 0.0679
-13.500 -0.9332 0.04887 0.04331 -0.0873 1.0000 0.0678
-13.250 -0.9716 0.04758 0.04191 -0.0802 1.0000 0.0678
-13.000 -1.0012 0.04574 0.03986 -0.0745 1.0000 0.0681
-12.750 -1.0244 0.04377 0.03761 -0.0694 1.0000 0.0684
-12.500 -1.0139 0.04211 0.03594 -0.0684 0.9988 0.0693
-12.250 -0.9836 0.04090 0.03475 -0.0704 0.9952 0.0705
-12.000 -0.9559 0.03942 0.03315 -0.0724 0.9916 0.0719
-11.750 -0.9347 0.03756 0.03104 -0.0735 0.9861 0.0735
-11.500 -0.9117 0.03545 0.02843 -0.0752 0.9815 0.0754
-11.250 -0.8814 0.03444 0.02758 -0.0764 0.9773 0.0771
-11.000 -0.8529 0.03357 0.02666 -0.0776 0.9722 0.0792
-10.750 -0.8216 0.03229 0.02508 -0.0795 0.9685 0.0820
-10.500 -0.7958 0.03109 0.02383 -0.0801 0.9632 0.0842
-10.250 -0.7650 0.03035 0.02311 -0.0813 0.9581 0.0867
-10.000 -0.7309 0.02937 0.02186 -0.0832 0.9546 0.0903
-9.750 -0.6975 0.02842 0.02098 -0.0849 0.9509 0.0935
-9.500 -0.6731 0.02783 0.02034 -0.0847 0.9435 0.0968
-9.250 -0.6378 0.02684 0.01918 -0.0867 0.9401 0.1010
-9.000 -0.5974 0.02614 0.01857 -0.0894 0.9378 0.1051
-8.750 -0.5778 0.02565 0.01790 -0.0881 0.9292 0.1088
-8.500 -0.5422 0.02479 0.01710 -0.0899 0.9254 0.1130
-8.250 -0.5026 0.02419 0.01644 -0.0924 0.9228 0.1180
-8.000 -0.4608 0.02333 0.01556 -0.0953 0.9210 0.1229
-7.750 -0.4416 0.02299 0.01524 -0.0937 0.9117 0.1266
-7.500 -0.4038 0.02246 0.01454 -0.0956 0.9081 0.1319
-7.250 -0.3637 0.02168 0.01391 -0.0981 0.9057 0.1374
-7.000 -0.3230 0.02115 0.01325 -0.1004 0.9036 0.1436
-6.750 -0.3033 0.02069 0.01288 -0.0989 0.8942 0.1479
-6.500 -0.2680 0.02020 0.01238 -0.1002 0.8899 0.1541
-6.250 -0.2303 0.01950 0.01167 -0.1019 0.8868 0.1605
-6.000 -0.2009 0.01911 0.01130 -0.1020 0.8808 0.1668
-5.750 -0.1738 0.01865 0.01080 -0.1017 0.8730 0.1736
-5.500 -0.1387 0.01810 0.01029 -0.1028 0.8688 0.1821
-5.250 -0.1080 0.01757 0.00978 -0.1031 0.8630 0.1914
-5.000 -0.0827 0.01726 0.00946 -0.1024 0.8541 0.2016
-4.750 -0.0492 0.01665 0.00891 -0.1033 0.8490 0.2145
-4.500 -0.0242 0.01630 0.00861 -0.1025 0.8402 0.2275
-4.250 0.0053 0.01595 0.00825 -0.1026 0.8326 0.2422
-4.000 0.0382 0.01562 0.00790 -0.1032 0.8266 0.2576
-3.750 0.0614 0.01543 0.00780 -0.1022 0.8158 0.2707
-3.500 0.0937 0.01512 0.00747 -0.1027 0.8092 0.2855
-3.250 0.1183 0.01503 0.00735 -0.1019 0.7985 0.2994
-3.000 0.1486 0.01474 0.00707 -0.1021 0.7906 0.3146
-2.750 0.1740 0.01455 0.00694 -0.1014 0.7805 0.3293
-2.500 0.2030 0.01432 0.00670 -0.1014 0.7717 0.3466
-2.250 0.2293 0.01418 0.00657 -0.1009 0.7617 0.3651
-2.000 0.2571 0.01396 0.00639 -0.1007 0.7523 0.3863
-1.750 0.2832 0.01379 0.00631 -0.1002 0.7426 0.4096
-1.500 0.3098 0.01358 0.00620 -0.0998 0.7329 0.4370
-1.250 0.3357 0.01344 0.00616 -0.0992 0.7233 0.4718
-1.000 0.3612 0.01325 0.00612 -0.0986 0.7136 0.5150
-0.750 0.3864 0.01309 0.00614 -0.0978 0.7044 0.5660
-0.500 0.4106 0.01293 0.00616 -0.0968 0.6945 0.6212
-0.250 0.4358 0.01283 0.00620 -0.0958 0.6858 0.6771
0.000 0.4588 0.01275 0.00629 -0.0944 0.6761 0.7305
0.250 0.4846 0.01273 0.00634 -0.0933 0.6681 0.7834
0.500 0.5069 0.01275 0.00650 -0.0916 0.6581 0.8310
0.750 0.5363 0.01285 0.00657 -0.0911 0.6504 0.8742
1.000 0.5650 0.01301 0.00677 -0.0907 0.6407 0.9113
1.250 0.6049 0.01318 0.00684 -0.0927 0.6323 0.9389
1.500 0.6459 0.01339 0.00701 -0.0951 0.6229 0.9619
1.750 0.6948 0.01357 0.00707 -0.0993 0.6139 0.9767
2.000 0.7474 0.01376 0.00719 -0.1044 0.6046 0.9886
2.250 0.8035 0.01389 0.00724 -0.1103 0.5951 0.9998
2.500 0.8236 0.01403 0.00728 -0.1091 0.5877 1.0000
2.750 0.8399 0.01415 0.00738 -0.1071 0.5794 1.0000
3.000 0.8616 0.01431 0.00742 -0.1060 0.5724 1.0000
3.250 0.8793 0.01449 0.00760 -0.1041 0.5646 1.0000
3.500 0.8989 0.01465 0.00771 -0.1026 0.5569 1.0000
3.750 0.9230 0.01488 0.00781 -0.1019 0.5502 1.0000
4.000 0.9397 0.01506 0.00803 -0.0998 0.5421 1.0000
4.250 0.9617 0.01525 0.00814 -0.0987 0.5348 1.0000
4.500 0.9829 0.01549 0.00835 -0.0974 0.5274 1.0000
4.750 1.0023 0.01568 0.00853 -0.0958 0.5192 1.0000
5.250 1.0452 0.01614 0.00892 -0.0933 0.5038 1.0000
5.500 1.0676 0.01635 0.00908 -0.0923 0.4964 1.0000
5.750 1.0910 0.01663 0.00932 -0.0915 0.4893 1.0000
6.000 1.1104 0.01686 0.00959 -0.0900 0.4814 1.0000
6.250 1.1355 0.01711 0.00975 -0.0895 0.4745 1.0000
6.500 1.1544 0.01740 0.01009 -0.0879 0.4669 1.0000
6.750 1.1752 0.01764 0.01033 -0.0866 0.4592 1.0000
7.000 1.1995 0.01795 0.01057 -0.0860 0.4522 1.0000
7.250 1.2161 0.01821 0.01091 -0.0840 0.4440 1.0000
7.500 1.2392 0.01849 0.01112 -0.0832 0.4367 1.0000
7.750 1.2561 0.01881 0.01150 -0.0814 0.4287 1.0000
8.000 1.2742 0.01908 0.01177 -0.0797 0.4207 1.0000
8.250 1.2930 0.01943 0.01210 -0.0782 0.4126 1.0000
8.500 1.3056 0.01971 0.01243 -0.0755 0.4037 1.0000
8.750 1.3221 0.02006 0.01272 -0.0736 0.3953 1.0000
9.000 1.3311 0.02043 0.01316 -0.0704 0.3863 1.0000
9.250 1.3475 0.02084 0.01351 -0.0687 0.3778 1.0000
9.500 1.3559 0.02131 0.01407 -0.0656 0.3685 1.0000
9.750 1.3702 0.02181 0.01450 -0.0636 0.3596 1.0000
10.000 1.3779 0.02239 0.01515 -0.0607 0.3496 1.0000
10.250 1.3880 0.02302 0.01577 -0.0583 0.3397 1.0000
10.500 1.3959 0.02374 0.01648 -0.0557 0.3292 1.0000
10.750 1.4037 0.02455 0.01734 -0.0533 0.3186 1.0000
11.250 1.4187 0.02641 0.01921 -0.0487 0.2980 1.0000
11.500 1.4259 0.02747 0.02025 -0.0466 0.2883 1.0000
11.750 1.4319 0.02865 0.02143 -0.0445 0.2783 1.0000
12.000 1.4381 0.02990 0.02272 -0.0426 0.2685 1.0000
12.250 1.4426 0.03130 0.02407 -0.0406 0.2593 1.0000
12.500 1.4478 0.03274 0.02559 -0.0389 0.2496 1.0000
12.750 1.4510 0.03435 0.02716 -0.0371 0.2409 1.0000
13.000 1.4546 0.03604 0.02891 -0.0356 0.2316 1.0000
13.250 1.4570 0.03788 0.03074 -0.0340 0.2233 1.0000
13.500 1.4586 0.03986 0.03275 -0.0327 0.2146 1.0000
13.750 1.4603 0.04193 0.03485 -0.0314 0.2063 1.0000
14.000 1.4598 0.04424 0.03714 -0.0302 0.1982 1.0000
14.250 1.4605 0.04657 0.03953 -0.0293 0.1899 1.0000
14.500 1.4581 0.04919 0.04211 -0.0283 0.1825 1.0000
14.750 1.4576 0.05183 0.04485 -0.0277 0.1743 1.0000
15.000 1.4541 0.05473 0.04769 -0.0269 0.1673 1.0000
15.250 1.4519 0.05769 0.05075 -0.0265 0.1594 1.0000
15.500 1.4480 0.06081 0.05385 -0.0261 0.1526 1.0000
15.750 1.4440 0.06408 0.05718 -0.0259 0.1453 1.0000
16.000 1.4398 0.06740 0.06051 -0.0257 0.1387 1.0000
16.250 1.4346 0.07091 0.06405 -0.0257 0.1323 1.0000
16.500 1.4301 0.07438 0.06755 -0.0258 0.1261 1.0000
16.750 1.4250 0.07796 0.07112 -0.0260 0.1206 1.0000
17.000 1.4213 0.08143 0.07464 -0.0262 0.1151 1.0000
17.250 1.4172 0.08497 0.07818 -0.0265 0.1104 1.0000
17.500 1.4149 0.08823 0.08145 -0.0267 0.1059 1.0000
17.750 1.4124 0.09165 0.08492 -0.0272 0.1019 1.0000
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