CLARK Y AIRFOIL (clarky-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK Y AIRFOIL (clarky-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.54 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarky-il-1000000-n5.txt Download as CSV file: xf-clarky-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.1702 0.03163 0.02850 -0.0911 1.0000 0.0115
-15.250 -1.1715 0.02989 0.02666 -0.0894 1.0000 0.0118
-15.000 -1.1655 0.02844 0.02510 -0.0880 1.0000 0.0121
-14.750 -1.1582 0.02720 0.02376 -0.0863 1.0000 0.0125
-14.500 -1.1508 0.02610 0.02256 -0.0842 1.0000 0.0128
-14.250 -1.1428 0.02512 0.02148 -0.0819 1.0000 0.0131
-14.000 -1.1202 0.02423 0.02053 -0.0821 0.9986 0.0136
-13.750 -1.0933 0.02347 0.01972 -0.0831 0.9967 0.0141
-13.500 -1.0657 0.02272 0.01891 -0.0840 0.9950 0.0147
-13.250 -1.0381 0.02196 0.01807 -0.0850 0.9934 0.0152
-13.000 -1.0123 0.02121 0.01722 -0.0855 0.9907 0.0157
-12.750 -0.9852 0.02049 0.01639 -0.0862 0.9882 0.0161
-12.500 -0.9573 0.01984 0.01568 -0.0869 0.9858 0.0166
-12.250 -0.9276 0.01939 0.01521 -0.0878 0.9838 0.0170
-12.000 -0.9001 0.01899 0.01478 -0.0882 0.9804 0.0174
-11.750 -0.8733 0.01857 0.01431 -0.0884 0.9762 0.0178
-11.500 -0.8450 0.01815 0.01383 -0.0890 0.9727 0.0183
-11.250 -0.8170 0.01772 0.01334 -0.0894 0.9692 0.0188
-11.000 -0.7918 0.01729 0.01284 -0.0892 0.9634 0.0192
-10.750 -0.7655 0.01683 0.01230 -0.0892 0.9583 0.0195
-10.500 -0.7398 0.01639 0.01177 -0.0890 0.9529 0.0197
-10.250 -0.7151 0.01589 0.01118 -0.0887 0.9463 0.0200
-10.000 -0.6903 0.01534 0.01057 -0.0885 0.9403 0.0205
-9.750 -0.6648 0.01500 0.01019 -0.0882 0.9333 0.0209
-9.500 -0.6389 0.01470 0.00983 -0.0879 0.9264 0.0212
-9.250 -0.6128 0.01441 0.00950 -0.0877 0.9193 0.0215
-9.000 -0.5868 0.01413 0.00915 -0.0874 0.9118 0.0220
-8.750 -0.5608 0.01378 0.00873 -0.0871 0.9043 0.0223
-8.500 -0.5348 0.01345 0.00833 -0.0868 0.8961 0.0227
-8.250 -0.5085 0.01315 0.00796 -0.0866 0.8880 0.0231
-7.750 -0.4558 0.01256 0.00720 -0.0861 0.8706 0.0238
-7.500 -0.4295 0.01224 0.00680 -0.0858 0.8622 0.0240
-7.250 -0.4028 0.01195 0.00643 -0.0856 0.8532 0.0241
-7.000 -0.3770 0.01150 0.00590 -0.0853 0.8448 0.0245
-6.750 -0.3510 0.01107 0.00540 -0.0850 0.8358 0.0249
-6.500 -0.3244 0.01077 0.00504 -0.0848 0.8276 0.0253
-6.250 -0.2975 0.01052 0.00473 -0.0846 0.8189 0.0257
-6.000 -0.2703 0.01031 0.00447 -0.0845 0.8107 0.0262
-5.750 -0.2431 0.01011 0.00422 -0.0843 0.8022 0.0266
-5.500 -0.2158 0.00989 0.00396 -0.0842 0.7939 0.0270
-5.250 -0.1887 0.00970 0.00370 -0.0840 0.7848 0.0275
-5.000 -0.1614 0.00952 0.00346 -0.0838 0.7738 0.0279
-4.750 -0.1342 0.00937 0.00324 -0.0836 0.7622 0.0283
-4.500 -0.1069 0.00923 0.00303 -0.0834 0.7516 0.0287
-4.250 -0.0794 0.00909 0.00284 -0.0833 0.7419 0.0291
-4.000 -0.0518 0.00898 0.00268 -0.0832 0.7320 0.0293
-3.750 -0.0246 0.00882 0.00245 -0.0830 0.7211 0.0300
-3.500 0.0029 0.00866 0.00226 -0.0829 0.7114 0.0309
-3.250 0.0305 0.00854 0.00210 -0.0827 0.7019 0.0319
-3.000 0.0580 0.00846 0.00197 -0.0826 0.6907 0.0329
-2.750 0.0856 0.00838 0.00185 -0.0825 0.6788 0.0340
-2.500 0.1132 0.00833 0.00174 -0.0823 0.6662 0.0349
-2.250 0.1408 0.00828 0.00165 -0.0822 0.6544 0.0358
-2.000 0.1684 0.00822 0.00156 -0.0821 0.6438 0.0386
-1.750 0.1961 0.00815 0.00148 -0.0820 0.6329 0.0423
-1.500 0.2234 0.00804 0.00141 -0.0819 0.6214 0.0602
-1.250 0.2508 0.00798 0.00137 -0.0818 0.6095 0.0762
-1.000 0.2782 0.00793 0.00132 -0.0816 0.5980 0.0919
-0.750 0.3056 0.00785 0.00129 -0.0815 0.5864 0.1132
-0.500 0.3329 0.00777 0.00126 -0.0814 0.5749 0.1433
-0.250 0.3600 0.00770 0.00125 -0.0813 0.5628 0.1790
0.000 0.3870 0.00766 0.00126 -0.0812 0.5493 0.2129
0.250 0.4139 0.00762 0.00128 -0.0810 0.5346 0.2531
0.500 0.4408 0.00759 0.00130 -0.0808 0.5202 0.2930
0.750 0.4677 0.00755 0.00134 -0.0807 0.5063 0.3373
1.000 0.4942 0.00746 0.00138 -0.0805 0.4918 0.4001
1.250 0.5201 0.00731 0.00144 -0.0803 0.4765 0.4975
1.500 0.5449 0.00708 0.00152 -0.0798 0.4599 0.6255
1.750 0.5682 0.00686 0.00162 -0.0789 0.4406 0.7615
2.000 0.5897 0.00675 0.00175 -0.0774 0.4180 0.8711
2.250 0.6146 0.00683 0.00190 -0.0765 0.3958 0.9468
2.500 0.6486 0.00702 0.00201 -0.0778 0.3762 0.9725
2.750 0.6817 0.00721 0.00212 -0.0791 0.3601 0.9846
3.000 0.7147 0.00740 0.00222 -0.0803 0.3467 0.9931
3.250 0.7516 0.00760 0.00235 -0.0824 0.3336 1.0000
3.500 0.7753 0.00780 0.00247 -0.0816 0.3202 1.0000
3.750 0.7996 0.00798 0.00258 -0.0809 0.3084 1.0000
4.000 0.8246 0.00813 0.00270 -0.0803 0.3007 1.0000
4.250 0.8496 0.00829 0.00282 -0.0798 0.2926 1.0000
4.500 0.8748 0.00845 0.00294 -0.0793 0.2843 1.0000
4.750 0.9001 0.00862 0.00307 -0.0788 0.2765 1.0000
5.000 0.9259 0.00876 0.00320 -0.0784 0.2715 1.0000
5.250 0.9518 0.00890 0.00333 -0.0781 0.2658 1.0000
5.500 0.9771 0.00909 0.00349 -0.0776 0.2584 1.0000
5.750 1.0028 0.00925 0.00364 -0.0773 0.2502 1.0000
6.000 1.0279 0.00947 0.00381 -0.0768 0.2402 1.0000
6.250 1.0522 0.00973 0.00401 -0.0762 0.2248 1.0000
6.500 1.0747 0.01014 0.00427 -0.0754 0.1985 1.0000
6.750 1.0958 0.01066 0.00462 -0.0744 0.1687 1.0000
7.000 1.1166 0.01119 0.00500 -0.0733 0.1428 1.0000
7.250 1.1378 0.01169 0.00539 -0.0723 0.1212 1.0000
7.500 1.1593 0.01216 0.00576 -0.0714 0.1046 1.0000
7.750 1.1812 0.01260 0.00612 -0.0705 0.0919 1.0000
8.000 1.2035 0.01298 0.00647 -0.0697 0.0833 1.0000
8.250 1.2259 0.01335 0.00681 -0.0689 0.0759 1.0000
8.500 1.2474 0.01377 0.00719 -0.0680 0.0685 1.0000
8.750 1.2690 0.01416 0.00755 -0.0671 0.0617 1.0000
9.000 1.2892 0.01464 0.00798 -0.0660 0.0525 1.0000
9.250 1.3062 0.01531 0.00855 -0.0644 0.0381 1.0000
9.750 1.3318 0.01691 0.01002 -0.0598 0.0134 1.0000
10.000 1.3485 0.01745 0.01059 -0.0582 0.0121 1.0000
10.250 1.3660 0.01794 0.01112 -0.0568 0.0115 1.0000
10.500 1.3826 0.01849 0.01170 -0.0552 0.0107 1.0000
10.750 1.3980 0.01911 0.01235 -0.0536 0.0100 1.0000
11.000 1.4125 0.01980 0.01308 -0.0519 0.0094 1.0000
11.250 1.4282 0.02043 0.01375 -0.0505 0.0090 1.0000
11.500 1.4429 0.02112 0.01449 -0.0490 0.0087 1.0000
11.750 1.4569 0.02188 0.01530 -0.0474 0.0083 1.0000
12.000 1.4699 0.02273 0.01618 -0.0459 0.0079 1.0000
12.250 1.4819 0.02367 0.01716 -0.0443 0.0076 1.0000
12.500 1.4923 0.02475 0.01831 -0.0427 0.0073 1.0000
12.750 1.5036 0.02580 0.01941 -0.0413 0.0071 1.0000
13.000 1.5150 0.02687 0.02054 -0.0399 0.0069 1.0000
13.250 1.5254 0.02804 0.02177 -0.0387 0.0067 1.0000
13.500 1.5350 0.02931 0.02310 -0.0374 0.0064 1.0000
13.750 1.5439 0.03069 0.02453 -0.0362 0.0062 1.0000
14.000 1.5518 0.03219 0.02610 -0.0351 0.0060 1.0000
14.250 1.5583 0.03385 0.02782 -0.0340 0.0059 1.0000
14.500 1.5636 0.03568 0.02972 -0.0330 0.0057 1.0000
14.750 1.5672 0.03773 0.03185 -0.0321 0.0055 1.0000
15.000 1.5681 0.04010 0.03430 -0.0312 0.0054 1.0000
15.250 1.5705 0.04240 0.03669 -0.0305 0.0053 1.0000
15.500 1.5729 0.04480 0.03917 -0.0300 0.0052 1.0000
15.750 1.5739 0.04741 0.04187 -0.0297 0.0052 1.0000
16.000 1.5736 0.05025 0.04480 -0.0295 0.0051 1.0000
16.250 1.5723 0.05332 0.04797 -0.0294 0.0050 1.0000
16.500 1.5699 0.05663 0.05137 -0.0296 0.0049 1.0000
16.750 1.5661 0.06018 0.05503 -0.0299 0.0049 1.0000
17.000 1.5607 0.06405 0.05900 -0.0304 0.0048 1.0000
17.250 1.5546 0.06813 0.06319 -0.0311 0.0047 1.0000
17.500 1.5467 0.07256 0.06772 -0.0321 0.0047 1.0000
17.750 1.5377 0.07721 0.07247 -0.0332 0.0046 1.0000
18.000 1.5270 0.08223 0.07761 -0.0345 0.0046 1.0000
18.250 1.5154 0.08748 0.08297 -0.0360 0.0045 1.0000
18.500 1.5025 0.09303 0.08864 -0.0378 0.0045 1.0000
18.750 1.4890 0.09873 0.09445 -0.0397 0.0045 1.0000
19.000 1.4743 0.10475 0.10058 -0.0419 0.0044 1.0000
19.250 1.4599 0.11079 0.10673 -0.0441 0.0044 1.0000
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