NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-018 (naca66-018-il) Reynolds number: 100,000 Max Cl/Cd: 31.61 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66-018-il-100000.txt Download as CSV file: xf-naca66-018-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-018
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6406 0.09431 0.08930 -0.0734 1.0000 0.1137
-13.250 -0.7033 0.08888 0.08379 -0.0736 1.0000 0.1134
-13.000 -0.7630 0.07726 0.07178 -0.0706 1.0000 0.0831
-12.750 -0.8003 0.07595 0.07044 -0.0650 1.0000 0.0827
-12.500 -0.8333 0.07430 0.06873 -0.0598 1.0000 0.0818
-12.250 -0.8685 0.07241 0.06673 -0.0542 1.0000 0.0808
-12.000 -0.9056 0.07049 0.06467 -0.0482 1.0000 0.0797
-11.750 -0.9470 0.06864 0.06262 -0.0412 1.0000 0.0782
-11.500 -1.0139 0.06749 0.06098 -0.0305 0.9968 0.0758
-11.250 -1.0132 0.06461 0.05779 -0.0284 0.9936 0.0730
-11.000 -1.0125 0.06109 0.05404 -0.0262 0.9909 0.0717
-10.750 -1.0136 0.05797 0.05063 -0.0235 0.9881 0.0703
-10.500 -1.0144 0.05502 0.04732 -0.0205 0.9856 0.0689
-10.250 -1.0107 0.05226 0.04413 -0.0179 0.9836 0.0678
-10.000 -1.0067 0.05013 0.04168 -0.0149 0.9818 0.0677
-9.750 -0.9978 0.04835 0.03967 -0.0126 0.9798 0.0687
-9.500 -0.9832 0.04649 0.03754 -0.0111 0.9777 0.0694
-9.250 -0.9628 0.04467 0.03543 -0.0104 0.9760 0.0703
-9.000 -0.9337 0.04278 0.03327 -0.0110 0.9749 0.0711
-8.750 -0.8905 0.04084 0.03106 -0.0138 0.9739 0.0727
-8.500 -0.7891 0.03794 0.02821 -0.0259 0.9737 0.0791
-8.250 -0.7452 0.03703 0.02724 -0.0284 0.9728 0.0841
-8.000 -0.7018 0.03604 0.02642 -0.0306 0.9721 0.0906
-7.750 -0.6868 0.03552 0.02590 -0.0290 0.9710 0.0972
-7.500 -0.6840 0.03483 0.02531 -0.0254 0.9700 0.1032
-7.250 -0.6847 0.03428 0.02476 -0.0213 0.9693 0.1097
-7.000 -0.6888 0.03354 0.02411 -0.0167 0.9683 0.1177
-6.750 -0.6956 0.03276 0.02343 -0.0117 0.9676 0.1312
-6.500 -0.7092 0.03188 0.02276 -0.0055 0.9684 0.1525
-6.250 -0.7315 0.03073 0.02206 0.0021 0.9703 0.1979
-6.000 -0.7626 0.02970 0.02135 0.0115 0.9728 0.2399
-5.750 -0.7961 0.02915 0.02073 0.0222 0.9788 0.2390
-5.500 -0.8326 0.02844 0.01989 0.0338 0.9904 0.2282
-5.250 -0.8647 0.02736 0.01879 0.0446 1.0000 0.2333
-5.000 -0.8842 0.02732 0.02164 0.0569 1.0000 0.6416
-4.750 -0.8940 0.02755 0.02172 0.0642 1.0000 0.6926
-4.500 -0.4462 0.05036 0.04352 0.0102 0.9670 0.7678
-4.250 -0.4423 0.05063 0.04371 0.0139 0.9681 0.7828
-4.000 -0.3798 0.05127 0.04419 0.0082 0.9669 0.7907
-3.750 -0.3646 0.05137 0.04421 0.0098 0.9672 0.8037
-3.500 -0.3606 0.05153 0.04431 0.0132 0.9687 0.8182
-3.250 -0.3128 0.05167 0.04433 0.0093 0.9681 0.8272
-3.000 -0.2881 0.05172 0.04431 0.0091 0.9678 0.8402
-2.750 -0.2793 0.05182 0.04436 0.0115 0.9695 0.8538
-2.500 -0.2480 0.05184 0.04431 0.0099 0.9697 0.8647
-2.250 -0.0258 0.05213 0.04445 -0.0234 0.9557 0.9504
-2.000 0.0131 0.05153 0.04381 -0.0275 0.9546 0.9673
-1.750 0.0535 0.05114 0.04338 -0.0321 0.9526 0.9832
-1.250 0.1409 0.04942 0.04161 -0.0431 0.9487 1.0000
-1.000 0.1567 0.04940 0.04158 -0.0429 0.9469 1.0000
-0.750 0.1671 0.04948 0.04166 -0.0417 0.9453 1.0000
-0.500 0.1679 0.04955 0.04175 -0.0385 0.9435 1.0000
-0.250 -0.0318 0.05143 0.04364 0.0028 0.9696 0.9601
0.000 0.0018 0.05122 0.04344 -0.0003 0.9666 0.9676
0.250 0.0326 0.05143 0.04364 -0.0029 0.9599 0.9693
0.500 0.0570 0.05128 0.04351 -0.0043 0.9548 0.9741
0.750 0.0864 0.05135 0.04360 -0.0066 0.9484 0.9761
1.250 0.1377 0.05139 0.04368 -0.0091 0.9256 0.9763
1.500 0.1846 0.05136 0.04370 -0.0141 0.9101 0.9808
1.750 0.1228 0.05199 0.04431 0.0002 0.9200 0.9643
2.000 0.1884 0.05172 0.04409 -0.0072 0.8908 0.9693
2.250 0.2135 0.05172 0.04413 -0.0078 0.8772 0.9687
2.500 0.2512 0.05184 0.04431 -0.0105 0.8649 0.9700
2.750 0.2778 0.05178 0.04432 -0.0112 0.8535 0.9694
3.000 0.2878 0.05169 0.04428 -0.0091 0.8400 0.9678
3.250 0.3135 0.05165 0.04431 -0.0094 0.8275 0.9680
3.500 0.3591 0.05149 0.04426 -0.0129 0.8179 0.9687
3.750 0.3625 0.05137 0.04420 -0.0095 0.8037 0.9672
4.000 0.3797 0.05125 0.04417 -0.0082 0.7909 0.9668
4.250 0.4393 0.05062 0.04371 -0.0134 0.7825 0.9679
4.500 0.4446 0.05033 0.04349 -0.0099 0.7676 0.9668
4.750 0.4585 0.05004 0.04330 -0.0078 0.7540 0.9666
5.000 0.4947 0.04924 0.04266 -0.0088 0.7429 0.9665
5.250 0.8645 0.02735 0.01878 -0.0446 0.2328 1.0000
5.500 0.8302 0.02847 0.01991 -0.0333 0.2279 0.9897
5.750 0.7964 0.02913 0.02071 -0.0223 0.2390 0.9789
6.000 0.7625 0.02967 0.02133 -0.0115 0.2416 0.9726
6.250 0.7321 0.03069 0.02203 -0.0022 0.1988 0.9703
6.500 0.7087 0.03189 0.02276 0.0056 0.1512 0.9684
6.750 0.6951 0.03277 0.02343 0.0118 0.1304 0.9676
7.000 0.6888 0.03351 0.02407 0.0168 0.1180 0.9682
7.250 0.6846 0.03426 0.02474 0.0213 0.1096 0.9693
7.500 0.6839 0.03483 0.02530 0.0254 0.1028 0.9700
7.750 0.6868 0.03550 0.02587 0.0290 0.0970 0.9710
8.000 0.7028 0.03604 0.02641 0.0305 0.0905 0.9721
8.250 0.7460 0.03702 0.02722 0.0283 0.0840 0.9728
8.500 0.7932 0.03799 0.02826 0.0253 0.0793 0.9737
8.750 0.8944 0.04094 0.03114 0.0131 0.0727 0.9740
9.000 0.9344 0.04277 0.03324 0.0109 0.0711 0.9749
9.250 0.9632 0.04466 0.03541 0.0104 0.0703 0.9760
9.500 0.9822 0.04645 0.03747 0.0113 0.0691 0.9777
9.750 0.9966 0.04814 0.03941 0.0127 0.0678 0.9797
10.000 1.0062 0.05009 0.04164 0.0150 0.0674 0.9818
10.250 1.0106 0.05223 0.04411 0.0179 0.0677 0.9837
10.500 1.0144 0.05504 0.04733 0.0205 0.0688 0.9857
10.750 1.0141 0.05798 0.05064 0.0234 0.0701 0.9882
11.000 1.0123 0.06104 0.05399 0.0262 0.0714 0.9910
11.250 1.0168 0.06462 0.05776 0.0278 0.0728 0.9935
11.500 1.0134 0.06742 0.06091 0.0306 0.0755 0.9969
11.750 0.9483 0.06852 0.06248 0.0410 0.0778 1.0000
12.000 0.9073 0.07032 0.06449 0.0481 0.0793 1.0000
12.250 0.8687 0.07232 0.06664 0.0543 0.0805 1.0000
12.500 0.8348 0.07417 0.06858 0.0597 0.0816 1.0000
12.750 0.8008 0.07564 0.07012 0.0651 0.0821 1.0000
13.000 0.7641 0.07690 0.07141 0.0707 0.0826 1.0000
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