CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.57 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkysm-il-1000000.txt Download as CSV file: xf-clarkysm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8294 0.05413 0.05180 -0.0742 1.0000 0.0116
-13.500 -0.9221 0.03549 0.03270 -0.0894 1.0000 0.0113
-13.250 -0.9533 0.03370 0.03082 -0.0836 1.0000 0.0113
-13.000 -0.9739 0.03227 0.02930 -0.0779 0.9998 0.0113
-12.750 -0.9521 0.03007 0.02693 -0.0803 0.9975 0.0115
-12.500 -0.9291 0.02813 0.02483 -0.0823 0.9951 0.0118
-12.250 -0.9066 0.02639 0.02292 -0.0837 0.9929 0.0120
-12.000 -0.8844 0.02488 0.02125 -0.0845 0.9898 0.0123
-11.750 -0.8583 0.02364 0.01987 -0.0856 0.9873 0.0125
-11.500 -0.8299 0.02259 0.01867 -0.0869 0.9856 0.0127
-11.250 -0.8002 0.02162 0.01758 -0.0883 0.9842 0.0129
-11.000 -0.7833 0.01941 0.01515 -0.0882 0.9801 0.0134
-10.750 -0.7559 0.01869 0.01438 -0.0887 0.9771 0.0139
-10.500 -0.7262 0.01797 0.01360 -0.0897 0.9751 0.0142
-10.250 -0.6949 0.01732 0.01287 -0.0909 0.9735 0.0147
-10.000 -0.6633 0.01659 0.01205 -0.0922 0.9723 0.0151
-9.750 -0.6304 0.01592 0.01129 -0.0936 0.9712 0.0156
-9.500 -0.6043 0.01542 0.01070 -0.0935 0.9669 0.0159
-9.250 -0.5777 0.01431 0.00947 -0.0939 0.9630 0.0165
-9.000 -0.5469 0.01367 0.00878 -0.0948 0.9601 0.0172
-8.750 -0.5135 0.01320 0.00827 -0.0962 0.9578 0.0178
-8.500 -0.4869 0.01279 0.00782 -0.0961 0.9521 0.0185
-8.250 -0.4579 0.01241 0.00736 -0.0964 0.9468 0.0191
-8.000 -0.4265 0.01186 0.00673 -0.0973 0.9425 0.0199
-7.750 -0.4037 0.01140 0.00624 -0.0963 0.9345 0.0209
-7.500 -0.3743 0.01107 0.00586 -0.0967 0.9286 0.0219
-7.250 -0.3487 0.01079 0.00553 -0.0961 0.9211 0.0229
-7.000 -0.3214 0.01050 0.00517 -0.0960 0.9139 0.0238
-6.750 -0.2972 0.01008 0.00472 -0.0952 0.9061 0.0255
-6.500 -0.2704 0.00988 0.00447 -0.0949 0.8985 0.0271
-6.250 -0.2443 0.00971 0.00425 -0.0945 0.8909 0.0285
-6.000 -0.2194 0.00936 0.00387 -0.0938 0.8829 0.0310
-5.750 -0.1934 0.00919 0.00367 -0.0933 0.8751 0.0330
-5.500 -0.1679 0.00895 0.00338 -0.0927 0.8670 0.0356
-5.250 -0.1421 0.00878 0.00321 -0.0922 0.8590 0.0387
-5.000 -0.1160 0.00863 0.00300 -0.0917 0.8509 0.0419
-4.750 -0.0904 0.00846 0.00284 -0.0912 0.8428 0.0458
-4.500 -0.0641 0.00836 0.00268 -0.0907 0.8345 0.0487
-4.250 -0.0387 0.00818 0.00251 -0.0901 0.8259 0.0541
-3.750 0.0131 0.00793 0.00223 -0.0890 0.8087 0.0640
-3.500 0.0394 0.00788 0.00212 -0.0885 0.7998 0.0682
-3.250 0.0645 0.00773 0.00197 -0.0878 0.7888 0.0762
-3.000 0.0900 0.00765 0.00186 -0.0872 0.7768 0.0831
-2.750 0.1154 0.00755 0.00175 -0.0865 0.7658 0.0922
-2.500 0.1408 0.00744 0.00165 -0.0859 0.7560 0.1050
-2.000 0.1914 0.00718 0.00149 -0.0847 0.7374 0.1517
-1.750 0.2165 0.00703 0.00143 -0.0840 0.7272 0.1873
-1.500 0.2415 0.00689 0.00138 -0.0834 0.7179 0.2275
-1.250 0.2664 0.00680 0.00135 -0.0827 0.7081 0.2639
-1.000 0.2915 0.00666 0.00132 -0.0821 0.6979 0.3047
-0.750 0.3160 0.00655 0.00130 -0.0813 0.6875 0.3508
-0.500 0.3396 0.00639 0.00128 -0.0804 0.6769 0.4167
-0.250 0.3627 0.00615 0.00129 -0.0794 0.6668 0.5038
0.000 0.3835 0.00588 0.00130 -0.0779 0.6563 0.6142
0.250 0.4013 0.00558 0.00133 -0.0756 0.6447 0.7378
0.500 0.4201 0.00531 0.00139 -0.0734 0.6335 0.8513
0.750 0.4687 0.00530 0.00153 -0.0777 0.6203 0.9392
1.000 0.5236 0.00545 0.00161 -0.0836 0.6063 0.9601
1.250 0.5640 0.00564 0.00173 -0.0862 0.5920 0.9756
1.500 0.6004 0.00581 0.00182 -0.0880 0.5769 0.9840
1.750 0.6403 0.00596 0.00189 -0.0906 0.5593 0.9883
2.000 0.6761 0.00612 0.00196 -0.0924 0.5427 0.9925
2.250 0.7124 0.00627 0.00203 -0.0943 0.5252 0.9954
2.500 0.7504 0.00642 0.00208 -0.0966 0.5064 0.9983
2.750 0.7842 0.00659 0.00215 -0.0980 0.4869 1.0000
3.000 0.8047 0.00673 0.00222 -0.0965 0.4686 1.0000
3.250 0.8250 0.00690 0.00230 -0.0949 0.4492 1.0000
3.500 0.8438 0.00713 0.00241 -0.0931 0.4248 1.0000
3.750 0.8633 0.00735 0.00252 -0.0914 0.4013 1.0000
4.000 0.8827 0.00758 0.00265 -0.0897 0.3807 1.0000
4.250 0.9021 0.00782 0.00279 -0.0879 0.3610 1.0000
4.500 0.9224 0.00803 0.00294 -0.0864 0.3467 1.0000
4.750 0.9431 0.00822 0.00308 -0.0849 0.3337 1.0000
5.000 0.9635 0.00842 0.00322 -0.0834 0.3205 1.0000
5.250 0.9841 0.00862 0.00337 -0.0820 0.3087 1.0000
5.500 1.0046 0.00883 0.00354 -0.0805 0.2988 1.0000
5.750 1.0254 0.00903 0.00370 -0.0791 0.2889 1.0000
6.000 1.0464 0.00921 0.00387 -0.0777 0.2802 1.0000
6.250 1.0667 0.00943 0.00405 -0.0762 0.2716 1.0000
6.500 1.0880 0.00960 0.00422 -0.0749 0.2636 1.0000
7.000 1.1292 0.01001 0.00459 -0.0721 0.2471 1.0000
7.250 1.1490 0.01026 0.00480 -0.0706 0.2374 1.0000
7.500 1.1680 0.01053 0.00503 -0.0689 0.2251 1.0000
7.750 1.1872 0.01080 0.00526 -0.0673 0.2122 1.0000
8.000 1.2046 0.01116 0.00554 -0.0654 0.1953 1.0000
8.250 1.2172 0.01168 0.00591 -0.0626 0.1671 1.0000
8.500 1.2219 0.01244 0.00644 -0.0584 0.1288 1.0000
8.750 1.2298 0.01313 0.00697 -0.0549 0.1044 1.0000
9.000 1.2425 0.01365 0.00743 -0.0523 0.0922 1.0000
9.250 1.2576 0.01409 0.00786 -0.0501 0.0844 1.0000
9.500 1.2718 0.01460 0.00833 -0.0479 0.0777 1.0000
9.750 1.2889 0.01497 0.00873 -0.0462 0.0743 1.0000
10.000 1.3045 0.01544 0.00919 -0.0443 0.0701 1.0000
10.250 1.3183 0.01602 0.00976 -0.0422 0.0654 1.0000
10.500 1.3362 0.01639 0.01018 -0.0408 0.0637 1.0000
10.750 1.3525 0.01685 0.01066 -0.0392 0.0613 1.0000
11.000 1.3670 0.01742 0.01123 -0.0374 0.0580 1.0000
11.250 1.3799 0.01811 0.01193 -0.0355 0.0550 1.0000
11.500 1.3972 0.01855 0.01243 -0.0342 0.0536 1.0000
11.750 1.4126 0.01911 0.01302 -0.0327 0.0518 1.0000
12.000 1.4263 0.01979 0.01371 -0.0311 0.0496 1.0000
12.250 1.4375 0.02064 0.01458 -0.0293 0.0468 1.0000
12.500 1.4520 0.02131 0.01530 -0.0279 0.0454 1.0000
12.750 1.4669 0.02196 0.01600 -0.0266 0.0438 1.0000
13.000 1.4794 0.02279 0.01686 -0.0252 0.0420 1.0000
13.250 1.4897 0.02380 0.01787 -0.0236 0.0396 1.0000
13.500 1.5005 0.02480 0.01892 -0.0222 0.0381 1.0000
13.750 1.5135 0.02567 0.01983 -0.0211 0.0364 1.0000
14.000 1.5237 0.02676 0.02096 -0.0198 0.0346 1.0000
14.250 1.5309 0.02812 0.02234 -0.0183 0.0325 1.0000
14.500 1.5402 0.02935 0.02364 -0.0172 0.0312 1.0000
14.750 1.5492 0.03065 0.02498 -0.0161 0.0296 1.0000
15.000 1.5554 0.03221 0.02657 -0.0150 0.0279 1.0000
15.250 1.5594 0.03400 0.02840 -0.0139 0.0261 1.0000
15.500 1.5662 0.03562 0.03008 -0.0130 0.0246 1.0000
15.750 1.5697 0.03759 0.03211 -0.0122 0.0234 1.0000
16.000 1.5689 0.04004 0.03460 -0.0113 0.0217 1.0000
16.250 1.5732 0.04207 0.03671 -0.0108 0.0206 1.0000
16.500 1.5741 0.04452 0.03922 -0.0103 0.0195 1.0000
16.750 1.5718 0.04740 0.04216 -0.0100 0.0185 1.0000
17.000 1.5683 0.05050 0.04533 -0.0099 0.0174 1.0000
17.250 1.5675 0.05339 0.04832 -0.0098 0.0169 1.0000
17.500 1.5645 0.05660 0.05161 -0.0100 0.0160 1.0000
17.750 1.5586 0.06028 0.05536 -0.0104 0.0154 1.0000
18.000 1.5493 0.06445 0.05963 -0.0110 0.0147 1.0000
18.250 1.5398 0.06879 0.06406 -0.0118 0.0144 1.0000
18.500 1.5329 0.07288 0.06825 -0.0127 0.0139 1.0000
18.750 1.5249 0.07717 0.07265 -0.0137 0.0136 1.0000
19.000 1.5151 0.08177 0.07735 -0.0149 0.0130 1.0000
19.250 1.5034 0.08675 0.08242 -0.0163 0.0128 1.0000
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Polar data table (+)
Polar graphs
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