CLARK Y AIRFOIL (clarky-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Y AIRFOIL (clarky-il) Reynolds number: 200,000 Max Cl/Cd: 73.15 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarky-il-200000.txt Download as CSV file: xf-clarky-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Y AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4082 0.09344 0.09005 -0.0468 1.0000 0.0739
-8.750 -0.4391 0.09151 0.08824 -0.0450 1.0000 0.0740
-8.500 -0.4670 0.08892 0.08571 -0.0443 1.0000 0.0741
-8.250 -0.4772 0.08456 0.08142 -0.0411 1.0000 0.0748
-8.000 -0.4670 0.08349 0.08039 -0.0352 1.0000 0.0758
-7.750 -0.4730 0.08209 0.07903 -0.0319 1.0000 0.0765
-7.500 -0.4528 0.07915 0.07607 -0.0338 0.9969 0.0785
-7.250 -0.4291 0.07367 0.07053 -0.0427 0.9910 0.0830
-7.000 -0.4158 0.06100 0.05751 -0.0619 0.9808 0.0895
-6.750 -0.3903 0.05905 0.05559 -0.0625 0.9760 0.0913
-6.500 -0.3615 0.05546 0.05190 -0.0668 0.9718 0.0951
-6.250 -0.3450 0.04808 0.04400 -0.0741 0.9623 0.1041
-6.000 -0.3240 0.03416 0.02886 -0.0789 0.9571 0.0704
-5.750 -0.3036 0.02800 0.02149 -0.0788 0.9496 0.0631
-5.500 -0.2702 0.02569 0.01892 -0.0806 0.9455 0.0638
-5.250 -0.2318 0.02391 0.01690 -0.0831 0.9428 0.0648
-5.000 -0.1910 0.02223 0.01497 -0.0858 0.9410 0.0653
-4.750 -0.1654 0.02118 0.01377 -0.0854 0.9327 0.0660
-4.500 -0.1273 0.02005 0.01249 -0.0874 0.9294 0.0673
-4.250 -0.0881 0.01908 0.01142 -0.0895 0.9268 0.0695
-4.000 -0.0604 0.01847 0.01072 -0.0893 0.9193 0.0719
-3.750 -0.0261 0.01778 0.00991 -0.0903 0.9145 0.0739
-3.500 0.0091 0.01659 0.00877 -0.0916 0.9112 0.0772
-3.250 0.0342 0.01609 0.00829 -0.0910 0.9027 0.0811
-3.000 0.0668 0.01553 0.00768 -0.0915 0.8975 0.0871
-2.750 0.0940 0.01485 0.00710 -0.0912 0.8900 0.0985
-2.500 0.1221 0.01403 0.00642 -0.0910 0.8825 0.1304
-2.250 0.1479 0.01328 0.00605 -0.0905 0.8741 0.2081
-2.000 0.1751 0.01271 0.00578 -0.0901 0.8662 0.2941
-1.750 0.1998 0.01226 0.00560 -0.0894 0.8568 0.3729
-1.500 0.2249 0.01156 0.00536 -0.0885 0.8491 0.4994
-1.250 0.2429 0.01087 0.00534 -0.0860 0.8383 0.6774
-1.000 0.2709 0.01036 0.00534 -0.0841 0.8309 0.8768
-0.750 0.3315 0.01030 0.00523 -0.0899 0.8231 0.9730
-0.500 0.3953 0.01014 0.00489 -0.0970 0.8170 1.0000
-0.250 0.4182 0.01015 0.00480 -0.0960 0.8055 1.0000
0.000 0.4424 0.01016 0.00470 -0.0952 0.7954 1.0000
0.250 0.4680 0.01015 0.00455 -0.0945 0.7864 1.0000
0.500 0.4915 0.01020 0.00453 -0.0935 0.7750 1.0000
0.750 0.5161 0.01024 0.00447 -0.0927 0.7644 1.0000
1.000 0.5419 0.01026 0.00437 -0.0920 0.7544 1.0000
1.250 0.5656 0.01032 0.00437 -0.0911 0.7423 1.0000
1.500 0.5899 0.01039 0.00437 -0.0902 0.7308 1.0000
1.750 0.6149 0.01046 0.00436 -0.0895 0.7196 1.0000
2.000 0.6402 0.01053 0.00433 -0.0887 0.7080 1.0000
2.250 0.6641 0.01061 0.00436 -0.0877 0.6945 1.0000
2.500 0.6883 0.01071 0.00440 -0.0868 0.6807 1.0000
2.750 0.7126 0.01081 0.00444 -0.0859 0.6666 1.0000
3.000 0.7370 0.01092 0.00449 -0.0851 0.6519 1.0000
3.250 0.7612 0.01104 0.00456 -0.0842 0.6360 1.0000
3.500 0.7852 0.01117 0.00462 -0.0832 0.6187 1.0000
3.750 0.8091 0.01133 0.00468 -0.0823 0.6003 1.0000
4.000 0.8324 0.01152 0.00480 -0.0812 0.5801 1.0000
4.250 0.8553 0.01174 0.00494 -0.0801 0.5580 1.0000
4.500 0.8781 0.01201 0.00508 -0.0790 0.5358 1.0000
4.750 0.9005 0.01231 0.00530 -0.0779 0.5124 1.0000
5.000 0.9227 0.01266 0.00551 -0.0768 0.4911 1.0000
5.250 0.9450 0.01300 0.00576 -0.0758 0.4700 1.0000
5.500 0.9671 0.01335 0.00602 -0.0747 0.4502 1.0000
5.750 0.9892 0.01371 0.00630 -0.0737 0.4321 1.0000
6.000 1.0116 0.01408 0.00660 -0.0727 0.4164 1.0000
6.250 1.0345 0.01444 0.00693 -0.0719 0.4033 1.0000
6.500 1.0576 0.01483 0.00730 -0.0711 0.3917 1.0000
6.750 1.0804 0.01525 0.00766 -0.0703 0.3808 1.0000
7.000 1.1032 0.01563 0.00805 -0.0695 0.3699 1.0000
7.250 1.1262 0.01602 0.00848 -0.0687 0.3598 1.0000
7.500 1.1486 0.01648 0.00890 -0.0679 0.3499 1.0000
7.750 1.1705 0.01686 0.00933 -0.0669 0.3391 1.0000
8.000 1.1918 0.01726 0.00978 -0.0659 0.3278 1.0000
8.250 1.2120 0.01769 0.01023 -0.0647 0.3155 1.0000
8.500 1.2310 0.01811 0.01066 -0.0634 0.3022 1.0000
8.750 1.2490 0.01852 0.01110 -0.0618 0.2876 1.0000
9.000 1.2663 0.01891 0.01155 -0.0602 0.2720 1.0000
9.250 1.2826 0.01932 0.01203 -0.0584 0.2533 1.0000
9.500 1.2960 0.01984 0.01253 -0.0563 0.2317 1.0000
9.750 1.3072 0.02048 0.01314 -0.0538 0.2074 1.0000
10.000 1.3158 0.02138 0.01392 -0.0512 0.1848 1.0000
10.250 1.3246 0.02239 0.01486 -0.0487 0.1663 1.0000
10.500 1.3333 0.02347 0.01590 -0.0464 0.1524 1.0000
10.750 1.3420 0.02458 0.01699 -0.0442 0.1408 1.0000
11.000 1.3494 0.02581 0.01818 -0.0421 0.1314 1.0000
11.250 1.3609 0.02682 0.01927 -0.0404 0.1222 1.0000
11.500 1.3704 0.02799 0.02047 -0.0387 0.1126 1.0000
11.750 1.3775 0.02935 0.02184 -0.0370 0.1040 1.0000
12.000 1.3859 0.03069 0.02323 -0.0355 0.0937 1.0000
12.250 1.3920 0.03227 0.02483 -0.0339 0.0811 1.0000
12.500 1.3965 0.03407 0.02662 -0.0324 0.0629 1.0000
12.750 1.3940 0.03655 0.02899 -0.0307 0.0468 1.0000
13.000 1.3907 0.03921 0.03163 -0.0292 0.0389 1.0000
13.250 1.3873 0.04198 0.03444 -0.0279 0.0350 1.0000
13.500 1.3833 0.04495 0.03749 -0.0269 0.0328 1.0000
13.750 1.3802 0.04793 0.04060 -0.0262 0.0311 1.0000
14.000 1.3753 0.05122 0.04401 -0.0257 0.0299 1.0000
14.250 1.3681 0.05491 0.04780 -0.0255 0.0289 1.0000
14.500 1.3581 0.05908 0.05208 -0.0256 0.0281 1.0000
14.750 1.3508 0.06309 0.05620 -0.0259 0.0275 1.0000
15.000 1.3451 0.06702 0.06027 -0.0263 0.0268 1.0000
15.250 1.3390 0.07109 0.06447 -0.0269 0.0262 1.0000
15.500 1.3327 0.07526 0.06876 -0.0276 0.0255 1.0000
15.750 1.3262 0.07955 0.07316 -0.0285 0.0250 1.0000
16.000 1.3199 0.08387 0.07756 -0.0294 0.0244 1.0000
16.250 1.3136 0.08815 0.08192 -0.0303 0.0239 1.0000
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