CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.42 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkx-il-1000000.txt Download as CSV file: xf-clarkx-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8537 0.09511 0.09300 -0.0420 1.0000 0.0171
-15.750 -1.0922 0.05111 0.04855 -0.0719 1.0000 0.0155
-15.500 -1.1502 0.03440 0.03138 -0.0898 1.0000 0.0153
-15.250 -1.1555 0.03165 0.02851 -0.0903 1.0000 0.0155
-15.000 -1.1562 0.02998 0.02674 -0.0888 1.0000 0.0157
-14.750 -1.1509 0.02865 0.02531 -0.0872 1.0000 0.0161
-14.500 -1.1432 0.02750 0.02406 -0.0855 1.0000 0.0165
-14.250 -1.1351 0.02651 0.02297 -0.0834 1.0000 0.0168
-14.000 -1.1259 0.02566 0.02202 -0.0812 1.0000 0.0171
-13.750 -1.1229 0.02450 0.02075 -0.0781 1.0000 0.0175
-13.500 -1.1185 0.02348 0.01966 -0.0750 1.0000 0.0180
-13.250 -1.1081 0.02289 0.01904 -0.0726 1.0000 0.0185
-13.000 -1.0839 0.02239 0.01851 -0.0726 0.9993 0.0191
-12.750 -1.0533 0.02185 0.01791 -0.0739 0.9980 0.0198
-12.500 -1.0225 0.02129 0.01726 -0.0752 0.9967 0.0204
-12.250 -0.9908 0.02080 0.01667 -0.0766 0.9954 0.0209
-12.000 -0.9629 0.01944 0.01521 -0.0780 0.9941 0.0219
-11.750 -0.9332 0.01896 0.01470 -0.0790 0.9922 0.0226
-11.500 -0.9025 0.01857 0.01428 -0.0800 0.9902 0.0233
-11.250 -0.8709 0.01819 0.01385 -0.0812 0.9884 0.0240
-11.000 -0.8383 0.01783 0.01341 -0.0825 0.9868 0.0248
-10.750 -0.8047 0.01756 0.01307 -0.0840 0.9856 0.0252
-10.500 -0.7751 0.01625 0.01165 -0.0855 0.9843 0.0264
-10.250 -0.7416 0.01581 0.01119 -0.0870 0.9833 0.0272
-10.000 -0.7127 0.01551 0.01086 -0.0875 0.9799 0.0280
-9.750 -0.6827 0.01519 0.01050 -0.0882 0.9767 0.0288
-9.500 -0.6518 0.01483 0.01008 -0.0890 0.9738 0.0296
-9.250 -0.6210 0.01449 0.00968 -0.0898 0.9711 0.0301
-9.000 -0.5964 0.01384 0.00893 -0.0894 0.9656 0.0308
-8.750 -0.5716 0.01316 0.00821 -0.0891 0.9600 0.0320
-8.500 -0.5439 0.01282 0.00785 -0.0891 0.9556 0.0328
-8.250 -0.5189 0.01256 0.00756 -0.0886 0.9487 0.0336
-8.000 -0.4923 0.01228 0.00722 -0.0883 0.9430 0.0345
-7.750 -0.4664 0.01198 0.00687 -0.0879 0.9365 0.0352
-7.500 -0.4401 0.01174 0.00656 -0.0876 0.9296 0.0359
-7.250 -0.4131 0.01157 0.00633 -0.0873 0.9232 0.0363
-7.000 -0.3895 0.01079 0.00547 -0.0866 0.9153 0.0378
-6.750 -0.3631 0.01047 0.00511 -0.0863 0.9086 0.0389
-6.500 -0.3364 0.01023 0.00485 -0.0861 0.9006 0.0400
-6.250 -0.3093 0.01004 0.00460 -0.0859 0.8936 0.0412
-6.000 -0.2822 0.00984 0.00436 -0.0856 0.8855 0.0423
-5.750 -0.2550 0.00967 0.00412 -0.0854 0.8782 0.0431
-5.500 -0.2285 0.00931 0.00371 -0.0852 0.8698 0.0446
-5.250 -0.2016 0.00905 0.00341 -0.0849 0.8621 0.0468
-5.000 -0.1742 0.00888 0.00323 -0.0848 0.8536 0.0486
-4.750 -0.1466 0.00876 0.00306 -0.0846 0.8459 0.0505
-4.500 -0.1188 0.00867 0.00293 -0.0845 0.8373 0.0518
-4.250 -0.0920 0.00838 0.00261 -0.0843 0.8294 0.0560
-4.000 -0.0644 0.00826 0.00247 -0.0842 0.8208 0.0590
-3.750 -0.0365 0.00818 0.00234 -0.0841 0.8127 0.0613
-3.500 -0.0092 0.00799 0.00214 -0.0839 0.8041 0.0663
-3.250 0.0185 0.00788 0.00202 -0.0838 0.7958 0.0709
-3.000 0.0462 0.00780 0.00189 -0.0837 0.7872 0.0753
-2.750 0.0738 0.00766 0.00177 -0.0836 0.7784 0.0827
-2.500 0.1012 0.00757 0.00166 -0.0834 0.7694 0.0912
-2.250 0.1288 0.00744 0.00157 -0.0833 0.7596 0.1050
-2.000 0.1561 0.00732 0.00149 -0.0832 0.7504 0.1281
-1.750 0.1834 0.00718 0.00141 -0.0830 0.7410 0.1539
-1.500 0.2106 0.00701 0.00134 -0.0829 0.7324 0.1899
-1.250 0.2373 0.00681 0.00131 -0.0828 0.7236 0.2538
-1.000 0.2650 0.00670 0.00129 -0.0827 0.7148 0.2895
-0.750 0.2923 0.00664 0.00127 -0.0826 0.7060 0.3188
-0.500 0.3199 0.00655 0.00125 -0.0825 0.6968 0.3487
-0.250 0.3470 0.00643 0.00124 -0.0824 0.6878 0.3926
0.000 0.3734 0.00622 0.00124 -0.0821 0.6781 0.4755
0.500 0.4237 0.00567 0.00129 -0.0811 0.6583 0.6972
0.750 0.4465 0.00539 0.00135 -0.0798 0.6463 0.8181
1.000 0.4689 0.00526 0.00144 -0.0783 0.6320 0.9113
1.250 0.5010 0.00533 0.00152 -0.0788 0.6167 0.9630
1.500 0.5389 0.00544 0.00157 -0.0809 0.6029 0.9835
1.750 0.5775 0.00554 0.00161 -0.0833 0.5902 0.9902
2.000 0.6158 0.00566 0.00166 -0.0856 0.5768 0.9954
2.250 0.6570 0.00578 0.00171 -0.0886 0.5614 0.9999
2.500 0.6817 0.00590 0.00176 -0.0879 0.5467 1.0000
2.750 0.7060 0.00602 0.00182 -0.0872 0.5322 1.0000
3.000 0.7302 0.00615 0.00189 -0.0864 0.5179 1.0000
3.250 0.7544 0.00629 0.00197 -0.0857 0.5032 1.0000
3.500 0.7786 0.00644 0.00206 -0.0849 0.4880 1.0000
3.750 0.8027 0.00660 0.00216 -0.0842 0.4723 1.0000
4.000 0.8267 0.00677 0.00227 -0.0834 0.4562 1.0000
4.250 0.8508 0.00695 0.00239 -0.0826 0.4392 1.0000
4.500 0.8747 0.00715 0.00252 -0.0818 0.4208 1.0000
4.750 0.8987 0.00737 0.00267 -0.0811 0.4021 1.0000
5.000 0.9224 0.00762 0.00283 -0.0803 0.3821 1.0000
5.250 0.9450 0.00796 0.00303 -0.0794 0.3519 1.0000
5.500 0.9679 0.00831 0.00324 -0.0785 0.3240 1.0000
5.750 0.9912 0.00862 0.00345 -0.0777 0.3033 1.0000
6.000 1.0151 0.00892 0.00367 -0.0771 0.2825 1.0000
6.250 1.0385 0.00924 0.00390 -0.0763 0.2617 1.0000
6.500 1.0616 0.00960 0.00415 -0.0756 0.2405 1.0000
6.750 1.0846 0.00996 0.00442 -0.0748 0.2198 1.0000
7.250 1.1297 0.01074 0.00501 -0.0732 0.1821 1.0000
7.500 1.1520 0.01114 0.00533 -0.0723 0.1639 1.0000
7.750 1.1731 0.01163 0.00570 -0.0713 0.1430 1.0000
8.000 1.1904 0.01239 0.00623 -0.0697 0.1036 1.0000
8.250 1.2006 0.01366 0.00714 -0.0671 0.0499 1.0000
8.500 1.2166 0.01447 0.00782 -0.0653 0.0315 1.0000
8.750 1.2355 0.01505 0.00838 -0.0639 0.0262 1.0000
9.000 1.2555 0.01552 0.00886 -0.0627 0.0237 1.0000
9.250 1.2729 0.01609 0.00944 -0.0611 0.0213 1.0000
9.500 1.2913 0.01652 0.00991 -0.0596 0.0201 1.0000
9.750 1.3083 0.01704 0.01045 -0.0580 0.0189 1.0000
10.000 1.3219 0.01779 0.01123 -0.0558 0.0176 1.0000
10.250 1.3387 0.01833 0.01182 -0.0543 0.0170 1.0000
10.500 1.3551 0.01890 0.01243 -0.0527 0.0163 1.0000
10.750 1.3707 0.01952 0.01308 -0.0511 0.0156 1.0000
11.000 1.3847 0.02025 0.01384 -0.0494 0.0149 1.0000
11.250 1.3931 0.02137 0.01502 -0.0470 0.0141 1.0000
11.500 1.4055 0.02225 0.01597 -0.0453 0.0138 1.0000
11.750 1.4189 0.02308 0.01685 -0.0438 0.0135 1.0000
12.000 1.4309 0.02402 0.01786 -0.0422 0.0131 1.0000
12.250 1.4422 0.02505 0.01894 -0.0406 0.0127 1.0000
12.500 1.4526 0.02617 0.02012 -0.0391 0.0123 1.0000
12.750 1.4620 0.02741 0.02142 -0.0376 0.0120 1.0000
13.000 1.4686 0.02890 0.02296 -0.0360 0.0117 1.0000
13.250 1.4700 0.03089 0.02504 -0.0343 0.0114 1.0000
13.500 1.4641 0.03362 0.02788 -0.0323 0.0111 1.0000
13.750 1.4730 0.03512 0.02945 -0.0314 0.0109 1.0000
14.000 1.4802 0.03683 0.03124 -0.0305 0.0108 1.0000
14.250 1.4854 0.03878 0.03326 -0.0297 0.0106 1.0000
14.500 1.4897 0.04086 0.03542 -0.0290 0.0103 1.0000
14.750 1.4922 0.04319 0.03785 -0.0283 0.0101 1.0000
15.000 1.4939 0.04570 0.04043 -0.0279 0.0099 1.0000
15.250 1.4944 0.04840 0.04322 -0.0275 0.0098 1.0000
15.500 1.4939 0.05132 0.04622 -0.0273 0.0096 1.0000
15.750 1.4924 0.05447 0.04946 -0.0274 0.0095 1.0000
16.000 1.4900 0.05782 0.05289 -0.0275 0.0093 1.0000
16.250 1.4857 0.06149 0.05664 -0.0279 0.0092 1.0000
16.500 1.4797 0.06549 0.06074 -0.0285 0.0091 1.0000
16.750 1.4714 0.06991 0.06526 -0.0293 0.0090 1.0000
17.000 1.4611 0.07468 0.07012 -0.0302 0.0089 1.0000
17.250 1.4483 0.07987 0.07542 -0.0314 0.0088 1.0000
17.500 1.4326 0.08553 0.08120 -0.0327 0.0087 1.0000
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Polar data table (+)
Polar graphs
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