CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 500,000 Max Cl/Cd: 90.19 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkysm-il-500000-n5.txt Download as CSV file: xf-clarkysm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7059 0.06877 0.06592 -0.0640 1.0000 0.0123
-13.000 -0.8376 0.04107 0.03784 -0.0855 1.0000 0.0116
-12.750 -0.8741 0.03732 0.03394 -0.0835 1.0000 0.0116
-12.500 -0.8870 0.03470 0.03113 -0.0815 0.9980 0.0117
-12.250 -0.8715 0.03180 0.02799 -0.0840 0.9935 0.0119
-12.000 -0.8563 0.02952 0.02548 -0.0849 0.9889 0.0121
-11.750 -0.8361 0.02759 0.02332 -0.0861 0.9853 0.0124
-11.500 -0.8141 0.02594 0.02144 -0.0870 0.9821 0.0126
-11.250 -0.7943 0.02457 0.01988 -0.0870 0.9770 0.0128
-11.000 -0.7712 0.02311 0.01828 -0.0876 0.9736 0.0132
-10.750 -0.7440 0.02199 0.01706 -0.0887 0.9713 0.0135
-10.500 -0.7218 0.02111 0.01606 -0.0884 0.9664 0.0138
-10.250 -0.6961 0.02027 0.01513 -0.0887 0.9625 0.0142
-10.000 -0.6675 0.01941 0.01415 -0.0895 0.9597 0.0146
-9.750 -0.6367 0.01857 0.01317 -0.0908 0.9576 0.0152
-9.500 -0.6119 0.01788 0.01237 -0.0906 0.9522 0.0156
-9.250 -0.5846 0.01715 0.01152 -0.0909 0.9476 0.0162
-9.000 -0.5543 0.01644 0.01075 -0.0919 0.9443 0.0168
-8.750 -0.5251 0.01589 0.01013 -0.0925 0.9400 0.0175
-8.500 -0.4984 0.01537 0.00952 -0.0925 0.9339 0.0181
-8.250 -0.4683 0.01481 0.00886 -0.0932 0.9293 0.0189
-8.000 -0.4404 0.01433 0.00829 -0.0933 0.9235 0.0195
-7.750 -0.4139 0.01380 0.00771 -0.0933 0.9167 0.0205
-7.500 -0.3840 0.01339 0.00724 -0.0938 0.9113 0.0216
-7.250 -0.3588 0.01305 0.00683 -0.0933 0.9035 0.0228
-7.000 -0.3307 0.01266 0.00635 -0.0934 0.8970 0.0239
-6.750 -0.3055 0.01230 0.00596 -0.0929 0.8891 0.0252
-6.500 -0.2783 0.01200 0.00559 -0.0927 0.8819 0.0268
-6.250 -0.2525 0.01173 0.00526 -0.0923 0.8741 0.0283
-6.000 -0.2262 0.01143 0.00493 -0.0919 0.8664 0.0306
-5.750 -0.2004 0.01120 0.00465 -0.0915 0.8585 0.0327
-5.500 -0.1742 0.01096 0.00435 -0.0910 0.8507 0.0350
-5.250 -0.1485 0.01074 0.00412 -0.0905 0.8427 0.0379
-5.000 -0.1221 0.01057 0.00388 -0.0901 0.8347 0.0407
-4.750 -0.0966 0.01036 0.00366 -0.0896 0.8265 0.0445
-4.500 -0.0702 0.01022 0.00346 -0.0892 0.8184 0.0480
-4.250 -0.0447 0.01003 0.00327 -0.0886 0.8098 0.0524
-3.750 0.0071 0.00975 0.00292 -0.0876 0.7928 0.0617
-3.500 0.0331 0.00964 0.00277 -0.0871 0.7842 0.0670
-3.250 0.0587 0.00950 0.00262 -0.0865 0.7747 0.0734
-3.000 0.0846 0.00940 0.00249 -0.0860 0.7657 0.0797
-2.750 0.1101 0.00928 0.00236 -0.0854 0.7560 0.0886
-2.500 0.1354 0.00918 0.00224 -0.0847 0.7440 0.0984
-2.250 0.1603 0.00908 0.00213 -0.0840 0.7301 0.1112
-2.000 0.1848 0.00898 0.00203 -0.0832 0.7155 0.1289
-1.500 0.2343 0.00876 0.00188 -0.0818 0.6926 0.1840
-1.250 0.2593 0.00865 0.00184 -0.0811 0.6817 0.2166
-1.000 0.2840 0.00855 0.00180 -0.0804 0.6708 0.2508
-0.750 0.3086 0.00848 0.00176 -0.0797 0.6597 0.2832
-0.500 0.3330 0.00837 0.00175 -0.0789 0.6477 0.3247
-0.250 0.3571 0.00825 0.00174 -0.0781 0.6366 0.3743
0.000 0.3800 0.00809 0.00174 -0.0771 0.6247 0.4419
0.250 0.4013 0.00787 0.00175 -0.0757 0.6123 0.5351
0.500 0.4209 0.00760 0.00178 -0.0740 0.5996 0.6438
0.750 0.4386 0.00729 0.00185 -0.0716 0.5882 0.7665
1.000 0.4993 0.00716 0.00208 -0.0784 0.5717 0.9314
1.250 0.5479 0.00734 0.00216 -0.0828 0.5538 0.9562
1.500 0.5823 0.00752 0.00224 -0.0842 0.5371 0.9692
1.750 0.6157 0.00769 0.00232 -0.0854 0.5213 0.9782
2.000 0.6485 0.00787 0.00240 -0.0865 0.5048 0.9862
2.250 0.6824 0.00806 0.00250 -0.0879 0.4870 0.9927
2.500 0.7210 0.00826 0.00260 -0.0904 0.4669 0.9986
2.750 0.7482 0.00845 0.00269 -0.0903 0.4484 1.0000
3.000 0.7685 0.00863 0.00280 -0.0888 0.4329 1.0000
3.250 0.7889 0.00881 0.00291 -0.0872 0.4180 1.0000
3.500 0.8092 0.00900 0.00303 -0.0857 0.4035 1.0000
3.750 0.8294 0.00921 0.00317 -0.0841 0.3889 1.0000
4.000 0.8496 0.00942 0.00332 -0.0826 0.3750 1.0000
4.250 0.8691 0.00966 0.00348 -0.0809 0.3578 1.0000
4.500 0.8882 0.00993 0.00365 -0.0792 0.3396 1.0000
4.750 0.9079 0.01018 0.00384 -0.0776 0.3253 1.0000
5.000 0.9275 0.01043 0.00402 -0.0760 0.3120 1.0000
5.250 0.9471 0.01069 0.00422 -0.0744 0.3006 1.0000
5.500 0.9679 0.01089 0.00441 -0.0730 0.2913 1.0000
5.750 0.9879 0.01113 0.00461 -0.0715 0.2822 1.0000
6.000 1.0076 0.01138 0.00483 -0.0699 0.2718 1.0000
6.250 1.0275 0.01163 0.00504 -0.0684 0.2612 1.0000
6.500 1.0469 0.01188 0.00528 -0.0668 0.2523 1.0000
6.750 1.0666 0.01212 0.00551 -0.0652 0.2435 1.0000
7.000 1.0859 0.01238 0.00575 -0.0636 0.2345 1.0000
7.250 1.1040 0.01269 0.00602 -0.0618 0.2228 1.0000
7.500 1.1209 0.01300 0.00630 -0.0598 0.2107 1.0000
7.750 1.1365 0.01333 0.00659 -0.0576 0.1967 1.0000
8.000 1.1504 0.01375 0.00693 -0.0551 0.1773 1.0000
8.250 1.1614 0.01434 0.00737 -0.0522 0.1507 1.0000
8.500 1.1703 0.01507 0.00794 -0.0490 0.1218 1.0000
8.750 1.1810 0.01576 0.00852 -0.0463 0.1034 1.0000
9.000 1.1949 0.01630 0.00904 -0.0441 0.0938 1.0000
9.250 1.2089 0.01686 0.00957 -0.0420 0.0863 1.0000
9.500 1.2234 0.01740 0.01012 -0.0400 0.0804 1.0000
9.750 1.2376 0.01797 0.01070 -0.0380 0.0757 1.0000
10.000 1.2529 0.01849 0.01125 -0.0363 0.0720 1.0000
10.250 1.2668 0.01910 0.01187 -0.0344 0.0684 1.0000
10.500 1.2799 0.01978 0.01257 -0.0325 0.0650 1.0000
10.750 1.2950 0.02035 0.01320 -0.0309 0.0629 1.0000
11.000 1.3088 0.02101 0.01390 -0.0293 0.0602 1.0000
11.250 1.3208 0.02181 0.01472 -0.0275 0.0572 1.0000
11.500 1.3325 0.02265 0.01559 -0.0258 0.0549 1.0000
11.750 1.3463 0.02338 0.01639 -0.0243 0.0530 1.0000
12.000 1.3586 0.02421 0.01728 -0.0228 0.0509 1.0000
12.250 1.3695 0.02518 0.01827 -0.0213 0.0484 1.0000
12.500 1.3784 0.02632 0.01943 -0.0197 0.0462 1.0000
12.750 1.3905 0.02726 0.02046 -0.0184 0.0449 1.0000
13.000 1.4013 0.02833 0.02159 -0.0172 0.0428 1.0000
13.250 1.4104 0.02955 0.02287 -0.0159 0.0409 1.0000
13.500 1.4178 0.03095 0.02430 -0.0146 0.0391 1.0000
13.750 1.4260 0.03233 0.02576 -0.0135 0.0376 1.0000
14.000 1.4342 0.03376 0.02726 -0.0125 0.0361 1.0000
14.250 1.4410 0.03533 0.02889 -0.0115 0.0343 1.0000
14.500 1.4458 0.03714 0.03076 -0.0106 0.0328 1.0000
14.750 1.4505 0.03902 0.03271 -0.0098 0.0313 1.0000
15.000 1.4556 0.04092 0.03469 -0.0092 0.0300 1.0000
15.250 1.4588 0.04306 0.03690 -0.0086 0.0283 1.0000
15.500 1.4604 0.04545 0.03935 -0.0082 0.0269 1.0000
15.750 1.4616 0.04797 0.04195 -0.0079 0.0258 1.0000
16.000 1.4629 0.05054 0.04461 -0.0077 0.0245 1.0000
16.250 1.4623 0.05339 0.04755 -0.0077 0.0234 1.0000
16.500 1.4597 0.05657 0.05080 -0.0078 0.0222 1.0000
16.750 1.4569 0.05987 0.05419 -0.0082 0.0212 1.0000
17.000 1.4538 0.06327 0.05768 -0.0086 0.0201 1.0000
17.250 1.4494 0.06693 0.06146 -0.0092 0.0197 1.0000
17.500 1.4432 0.07089 0.06550 -0.0100 0.0186 1.0000
17.750 1.4358 0.07513 0.06984 -0.0110 0.0180 1.0000
18.000 1.4278 0.07950 0.07430 -0.0121 0.0174 1.0000
18.250 1.4205 0.08385 0.07877 -0.0133 0.0170 1.0000
18.500 1.4123 0.08840 0.08343 -0.0147 0.0165 1.0000
18.750 1.4027 0.09324 0.08838 -0.0162 0.0160 1.0000
19.000 1.3923 0.09823 0.09346 -0.0179 0.0153 1.0000
19.250 1.3814 0.10338 0.09870 -0.0198 0.0149 1.0000
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Polar data table (+)
Polar graphs
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