CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 500,000 Max Cl/Cd: 103.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkx-il-500000.txt Download as CSV file: xf-clarkx-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK X AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8243 0.04031 0.03732 -0.0811 1.0000 0.0266
-11.750 -0.8299 0.03906 0.03601 -0.0782 1.0000 0.0269
-11.500 -0.8366 0.03782 0.03470 -0.0747 1.0000 0.0272
-11.250 -0.8422 0.03657 0.03335 -0.0711 1.0000 0.0276
-11.000 -0.8469 0.03514 0.03180 -0.0676 1.0000 0.0280
-10.750 -0.8294 0.03249 0.02884 -0.0692 0.9976 0.0290
-10.500 -0.8039 0.03012 0.02608 -0.0715 0.9948 0.0300
-10.250 -0.7823 0.02715 0.02279 -0.0733 0.9917 0.0312
-10.000 -0.7505 0.02674 0.02241 -0.0749 0.9890 0.0320
-9.750 -0.7182 0.02614 0.02174 -0.0766 0.9866 0.0330
-9.500 -0.6861 0.02506 0.02050 -0.0786 0.9846 0.0342
-9.250 -0.6530 0.02393 0.01914 -0.0806 0.9830 0.0355
-9.000 -0.6249 0.02337 0.01836 -0.0811 0.9784 0.0363
-8.750 -0.5982 0.02088 0.01568 -0.0825 0.9752 0.0377
-8.500 -0.5637 0.02031 0.01509 -0.0844 0.9733 0.0388
-8.250 -0.5280 0.01974 0.01443 -0.0864 0.9719 0.0401
-8.000 -0.4927 0.01891 0.01348 -0.0884 0.9705 0.0414
-7.750 -0.4658 0.01820 0.01262 -0.0884 0.9649 0.0424
-7.500 -0.4335 0.01780 0.01209 -0.0894 0.9612 0.0433
-7.250 -0.4040 0.01606 0.01022 -0.0904 0.9581 0.0449
-7.000 -0.3748 0.01545 0.00958 -0.0908 0.9538 0.0461
-6.750 -0.3480 0.01496 0.00906 -0.0906 0.9474 0.0473
-6.500 -0.3184 0.01451 0.00854 -0.0910 0.9429 0.0489
-6.250 -0.2922 0.01408 0.00803 -0.0906 0.9363 0.0502
-6.000 -0.2652 0.01367 0.00754 -0.0903 0.9298 0.0513
-5.750 -0.2393 0.01289 0.00668 -0.0899 0.9238 0.0528
-5.500 -0.2146 0.01233 0.00611 -0.0893 0.9159 0.0548
-5.250 -0.1872 0.01202 0.00577 -0.0891 0.9100 0.0569
-5.000 -0.1615 0.01175 0.00546 -0.0886 0.9015 0.0592
-4.750 -0.1340 0.01150 0.00512 -0.0883 0.8951 0.0612
-4.500 -0.1092 0.01096 0.00456 -0.0877 0.8865 0.0643
-4.250 -0.0821 0.01066 0.00425 -0.0874 0.8796 0.0676
-4.000 -0.0556 0.01046 0.00401 -0.0870 0.8711 0.0712
-3.750 -0.0285 0.01017 0.00366 -0.0867 0.8639 0.0756
-3.500 -0.0021 0.00992 0.00343 -0.0864 0.8552 0.0811
-3.250 0.0256 0.00978 0.00320 -0.0862 0.8480 0.0858
-3.000 0.0519 0.00949 0.00296 -0.0859 0.8391 0.0945
-2.750 0.0792 0.00930 0.00275 -0.0857 0.8316 0.1050
-2.500 0.1060 0.00909 0.00261 -0.0854 0.8226 0.1213
-2.250 0.1331 0.00889 0.00245 -0.0852 0.8147 0.1474
-2.000 0.1593 0.00859 0.00232 -0.0849 0.8055 0.1909
-1.750 0.1856 0.00831 0.00226 -0.0846 0.7968 0.2641
-1.500 0.2124 0.00815 0.00219 -0.0844 0.7875 0.3093
-1.250 0.2391 0.00800 0.00213 -0.0841 0.7778 0.3488
-1.000 0.2657 0.00783 0.00206 -0.0838 0.7691 0.3961
-0.750 0.2913 0.00754 0.00204 -0.0834 0.7594 0.4783
-0.500 0.3154 0.00716 0.00203 -0.0827 0.7508 0.6015
-0.250 0.3377 0.00676 0.00207 -0.0813 0.7415 0.7362
0.000 0.3595 0.00650 0.00215 -0.0795 0.7326 0.8565
0.250 0.3897 0.00648 0.00221 -0.0794 0.7236 0.9302
0.500 0.4305 0.00654 0.00225 -0.0818 0.7136 0.9699
0.750 0.4814 0.00662 0.00226 -0.0866 0.7037 0.9900
1.000 0.5286 0.00668 0.00223 -0.0908 0.6928 0.9994
1.250 0.5552 0.00673 0.00223 -0.0906 0.6807 1.0000
1.500 0.5796 0.00680 0.00223 -0.0898 0.6672 1.0000
1.750 0.6040 0.00688 0.00224 -0.0891 0.6532 1.0000
2.000 0.6285 0.00697 0.00226 -0.0883 0.6406 1.0000
2.250 0.6528 0.00708 0.00230 -0.0876 0.6280 1.0000
2.500 0.6773 0.00718 0.00235 -0.0869 0.6152 1.0000
2.750 0.7018 0.00728 0.00241 -0.0861 0.6023 1.0000
3.000 0.7261 0.00740 0.00249 -0.0854 0.5889 1.0000
3.250 0.7502 0.00754 0.00257 -0.0845 0.5746 1.0000
3.500 0.7741 0.00769 0.00266 -0.0837 0.5594 1.0000
3.750 0.7980 0.00785 0.00277 -0.0829 0.5439 1.0000
4.000 0.8220 0.00802 0.00289 -0.0821 0.5285 1.0000
4.250 0.8460 0.00821 0.00302 -0.0813 0.5124 1.0000
4.500 0.8700 0.00841 0.00316 -0.0805 0.4958 1.0000
4.750 0.8938 0.00862 0.00333 -0.0797 0.4785 1.0000
5.000 0.9175 0.00886 0.00350 -0.0789 0.4605 1.0000
5.250 0.9408 0.00912 0.00369 -0.0781 0.4416 1.0000
5.500 0.9643 0.00938 0.00390 -0.0773 0.4209 1.0000
5.750 0.9864 0.00974 0.00414 -0.0762 0.3959 1.0000
6.000 1.0083 0.01011 0.00439 -0.0752 0.3677 1.0000
6.250 1.0303 0.01050 0.00467 -0.0742 0.3419 1.0000
6.500 1.0518 0.01092 0.00497 -0.0732 0.3178 1.0000
6.750 1.0741 0.01129 0.00527 -0.0723 0.2958 1.0000
7.000 1.0958 0.01171 0.00559 -0.0713 0.2749 1.0000
7.250 1.1175 0.01213 0.00594 -0.0704 0.2537 1.0000
7.500 1.1385 0.01258 0.00630 -0.0693 0.2318 1.0000
7.750 1.1590 0.01307 0.00669 -0.0682 0.2110 1.0000
8.000 1.1795 0.01355 0.00711 -0.0671 0.1915 1.0000
8.250 1.1982 0.01415 0.00758 -0.0658 0.1697 1.0000
8.500 1.2151 0.01486 0.00813 -0.0642 0.1379 1.0000
8.750 1.2179 0.01652 0.00927 -0.0606 0.0646 1.0000
9.000 1.2241 0.01777 0.01032 -0.0573 0.0388 1.0000
9.250 1.2363 0.01864 0.01119 -0.0549 0.0333 1.0000
9.500 1.2504 0.01939 0.01200 -0.0529 0.0304 1.0000
9.750 1.2631 0.02024 0.01289 -0.0508 0.0282 1.0000
10.000 1.2720 0.02135 0.01405 -0.0483 0.0262 1.0000
10.250 1.2859 0.02214 0.01490 -0.0466 0.0249 1.0000
10.500 1.2979 0.02306 0.01590 -0.0447 0.0237 1.0000
10.750 1.3071 0.02420 0.01709 -0.0427 0.0227 1.0000
11.000 1.3093 0.02588 0.01883 -0.0401 0.0218 1.0000
11.250 1.3167 0.02725 0.02028 -0.0381 0.0212 1.0000
11.500 1.3260 0.02852 0.02164 -0.0365 0.0206 1.0000
11.750 1.3340 0.02994 0.02314 -0.0350 0.0200 1.0000
12.000 1.3412 0.03146 0.02474 -0.0335 0.0193 1.0000
12.250 1.3473 0.03313 0.02647 -0.0322 0.0187 1.0000
12.500 1.3507 0.03509 0.02848 -0.0308 0.0182 1.0000
12.750 1.3480 0.03768 0.03114 -0.0292 0.0177 1.0000
13.000 1.3470 0.04019 0.03374 -0.0279 0.0173 1.0000
13.250 1.3525 0.04216 0.03582 -0.0270 0.0170 1.0000
13.500 1.3564 0.04434 0.03810 -0.0262 0.0167 1.0000
13.750 1.3593 0.04665 0.04050 -0.0254 0.0164 1.0000
14.000 1.3615 0.04908 0.04303 -0.0248 0.0161 1.0000
14.250 1.3635 0.05160 0.04564 -0.0243 0.0158 1.0000
14.500 1.3651 0.05423 0.04835 -0.0239 0.0155 1.0000
14.750 1.3663 0.05695 0.05115 -0.0236 0.0152 1.0000
15.000 1.3672 0.05975 0.05403 -0.0234 0.0149 1.0000
15.250 1.3676 0.06265 0.05699 -0.0233 0.0147 1.0000
15.500 1.3675 0.06560 0.06000 -0.0231 0.0145 1.0000
15.750 1.3664 0.06845 0.06289 -0.0222 0.0141 1.0000
16.000 1.3648 0.07165 0.06622 -0.0219 0.0139 1.0000
16.250 1.3630 0.07524 0.06995 -0.0227 0.0138 1.0000
16.500 1.3606 0.07893 0.07379 -0.0235 0.0136 1.0000
16.750 1.3574 0.08278 0.07778 -0.0243 0.0134 1.0000
17.000 1.3535 0.08677 0.08190 -0.0253 0.0132 1.0000
17.250 1.3490 0.09093 0.08620 -0.0264 0.0130 1.0000
17.500 1.3437 0.09529 0.09070 -0.0277 0.0129 1.0000
17.750 1.3376 0.09984 0.09538 -0.0291 0.0128 1.0000
18.000 1.3306 0.10461 0.10029 -0.0309 0.0126 1.0000
18.250 1.3230 0.10962 0.10543 -0.0329 0.0125 1.0000
18.500 1.3147 0.11486 0.11082 -0.0351 0.0124 1.0000
18.750 1.3056 0.12036 0.11645 -0.0377 0.0124 1.0000
19.000 1.2958 0.12611 0.12234 -0.0406 0.0123 1.0000
19.250 1.2847 0.13227 0.12866 -0.0439 0.0122 1.0000
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