NACA 66(3)-418 (naca663418-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(3)-418 (naca663418-il) Reynolds number: 100,000 Max Cl/Cd: 26.98 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca663418-il-100000.txt Download as CSV file: xf-naca663418-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-418
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4357 0.11086 0.10619 -0.0684 0.9654 0.1891
-10.500 -0.4154 0.10938 0.10467 -0.0664 0.9637 0.1944
-10.250 -0.4769 0.10373 0.09917 -0.0689 0.9615 0.2047
-10.000 -0.4339 0.10286 0.09823 -0.0665 0.9603 0.2096
-7.500 -0.9366 0.05847 0.05147 -0.0044 1.0000 0.0924
-7.250 -0.9270 0.05485 0.04765 -0.0026 1.0000 0.0902
-7.000 -0.9180 0.05088 0.04319 -0.0002 1.0000 0.0855
-6.750 -0.9056 0.04875 0.04017 0.0029 1.0000 0.0807
-6.500 -0.8892 0.04598 0.03721 0.0041 1.0000 0.0797
-6.250 -0.8720 0.04377 0.03473 0.0055 1.0000 0.0791
-6.000 -0.8537 0.04192 0.03260 0.0068 1.0000 0.0789
-5.750 -0.8350 0.04049 0.03090 0.0081 1.0000 0.0795
-5.500 -0.8160 0.03943 0.02955 0.0094 1.0000 0.0806
-5.250 -0.7960 0.03804 0.02799 0.0104 1.0000 0.0819
-5.000 -0.7749 0.03667 0.02659 0.0113 1.0000 0.0830
-4.750 -0.7544 0.03566 0.02559 0.0122 1.0000 0.0847
-4.500 -0.7344 0.03488 0.02480 0.0133 1.0000 0.0869
-4.250 -0.7151 0.03430 0.02417 0.0144 1.0000 0.0903
-4.000 -0.6958 0.03385 0.02362 0.0155 1.0000 0.0938
-3.750 -0.6781 0.03299 0.02293 0.0168 1.0000 0.0976
-3.500 -0.6609 0.03244 0.02245 0.0181 1.0000 0.1026
-3.250 -0.6437 0.03196 0.02195 0.0194 1.0000 0.1093
-3.000 -0.6207 0.03169 0.02176 0.0194 0.9980 0.1224
-2.750 -0.5962 0.03135 0.02170 0.0191 0.9953 0.1532
-2.500 -0.6026 0.02997 0.02364 0.0270 0.9941 0.7088
-2.250 -0.5925 0.03247 0.02608 0.0337 0.9882 0.7712
-2.000 -0.5766 0.03534 0.02890 0.0392 0.9835 0.8025
-1.750 -0.5673 0.03642 0.02990 0.0445 0.9775 0.8270
-1.500 -0.3833 0.04703 0.04028 0.0283 0.9908 0.9225
-1.250 -0.3244 0.04797 0.04104 0.0210 0.9876 0.9316
-1.000 -0.2873 0.04886 0.04179 0.0174 0.9836 0.9382
-0.750 -0.2542 0.04891 0.04171 0.0146 0.9774 0.9429
-0.500 -0.2292 0.04972 0.04242 0.0133 0.9717 0.9485
-0.250 -0.1963 0.04967 0.04229 0.0104 0.9652 0.9517
0.000 -0.1585 0.05047 0.04299 0.0066 0.9590 0.9552
0.250 -0.1431 0.05045 0.04292 0.0071 0.9518 0.9586
0.500 -0.1169 0.05113 0.04352 0.0057 0.9446 0.9612
0.750 -0.0942 0.05119 0.04355 0.0047 0.9372 0.9633
1.000 -0.0608 0.05191 0.04421 0.0018 0.9297 0.9651
1.250 -0.0458 0.05207 0.04434 0.0024 0.9223 0.9670
1.500 -0.0182 0.05266 0.04490 0.0007 0.9139 0.9687
1.750 -0.0074 0.05290 0.04513 0.0021 0.9065 0.9706
2.000 0.0169 0.05344 0.04564 0.0012 0.8972 0.9719
2.250 0.0299 0.05370 0.04589 0.0021 0.8892 0.9734
2.500 0.0611 0.05442 0.04659 -0.0001 0.8799 0.9742
2.750 0.0730 0.05457 0.04676 0.0009 0.8702 0.9756
3.000 0.1130 0.05575 0.04793 -0.0027 0.8617 0.9768
3.250 0.1176 0.05552 0.04772 -0.0003 0.8493 0.9778
3.500 0.1587 0.05716 0.04937 -0.0039 0.8425 0.9785
3.750 0.1968 0.05755 0.04977 -0.0063 0.8259 0.9796
4.000 0.2404 0.05503 0.04725 -0.0071 0.7812 0.9805
4.250 0.2678 0.05495 0.04719 -0.0075 0.7670 0.9818
4.500 0.3196 0.05509 0.04737 -0.0114 0.7595 0.9825
4.750 0.3258 0.05494 0.04726 -0.0090 0.7458 0.9840
5.000 0.3462 0.05504 0.04743 -0.0089 0.7335 0.9853
5.250 0.3950 0.05500 0.04746 -0.0125 0.7275 0.9862
5.500 0.4097 0.05511 0.04764 -0.0117 0.7142 0.9882
5.750 0.4339 0.05522 0.04784 -0.0121 0.7027 0.9903
6.000 0.4798 0.05484 0.04757 -0.0150 0.6962 0.9919
6.250 0.4949 0.05496 0.04777 -0.0141 0.6834 0.9939
6.500 0.5439 0.05428 0.04722 -0.0171 0.6776 0.9952
6.750 0.5667 0.05415 0.04721 -0.0172 0.6654 0.9974
7.000 0.5887 0.05418 0.04737 -0.0173 0.6532 0.9997
7.250 0.6338 0.05276 0.04609 -0.0188 0.6484 1.0000
7.500 0.6346 0.05256 0.04597 -0.0150 0.6352 1.0000
8.750 0.7807 0.03860 0.03266 -0.0042 0.5731 1.0000
9.000 0.7884 0.03696 0.03110 0.0000 0.5579 1.0000
9.250 0.8028 0.03491 0.02913 0.0038 0.5390 1.0000
9.500 0.8200 0.03301 0.02724 0.0070 0.5077 1.0000
9.750 0.8431 0.03125 0.02519 0.0097 0.4370 1.0000
10.000 0.8386 0.03195 0.02499 0.0141 0.3122 1.0000
10.250 0.8162 0.03484 0.02691 0.0184 0.1960 1.0000
10.500 0.8055 0.03763 0.02897 0.0213 0.1318 1.0000
10.750 0.8091 0.03960 0.03065 0.0227 0.1095 1.0000
11.000 0.8203 0.04111 0.03205 0.0236 0.0967 1.0000
11.250 0.8382 0.04229 0.03317 0.0241 0.0875 1.0000
11.500 0.8632 0.04327 0.03401 0.0241 0.0801 1.0000
11.750 0.8942 0.04413 0.03484 0.0236 0.0743 1.0000
12.000 0.9457 0.04503 0.03563 0.0216 0.0695 1.0000
12.250 0.9796 0.04636 0.03709 0.0206 0.0659 1.0000
12.500 1.0213 0.04796 0.03868 0.0187 0.0625 1.0000
12.750 1.0824 0.05101 0.04185 0.0150 0.0607 1.0000
13.000 1.1023 0.05360 0.04478 0.0151 0.0602 1.0000
13.250 1.1152 0.05643 0.04797 0.0158 0.0598 1.0000
13.500 1.1212 0.05936 0.05123 0.0169 0.0596 1.0000
13.750 1.1205 0.06237 0.05456 0.0185 0.0593 1.0000
14.000 1.1157 0.06555 0.05805 0.0202 0.0591 1.0000
14.250 1.1060 0.06895 0.06175 0.0219 0.0590 1.0000
14.500 1.0955 0.07264 0.06572 0.0234 0.0591 1.0000
14.750 1.0820 0.07669 0.07003 0.0246 0.0594 1.0000
15.000 1.0696 0.08101 0.07458 0.0254 0.0599 1.0000
15.250 1.0621 0.08578 0.07952 0.0257 0.0605 1.0000
15.500 1.0617 0.09086 0.08476 0.0254 0.0612 1.0000
15.750 1.0040 0.09569 0.09001 0.0261 0.0622 1.0000
16.000 0.8976 0.10994 0.10486 0.0210 0.0654 1.0000
16.250 0.8423 0.12348 0.11859 0.0138 0.0684 1.0000
16.500 0.8314 0.13099 0.12612 0.0103 0.0701 1.0000
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Polar data table (+)
Polar graphs
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