CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.92 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkx-il-1000000-n5.txt Download as CSV file: xf-clarkx-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6969 0.13016 0.12825 -0.0231 1.0000 0.0131
-16.000 -1.1702 0.03799 0.03487 -0.0873 1.0000 0.0090
-15.750 -1.1880 0.03307 0.02975 -0.0907 1.0000 0.0091
-15.500 -1.1967 0.03055 0.02709 -0.0897 1.0000 0.0093
-15.250 -1.1979 0.02872 0.02514 -0.0878 1.0000 0.0095
-15.000 -1.1936 0.02718 0.02348 -0.0861 1.0000 0.0098
-14.750 -1.1876 0.02590 0.02211 -0.0840 1.0000 0.0102
-14.500 -1.1803 0.02481 0.02092 -0.0818 1.0000 0.0106
-14.250 -1.1687 0.02381 0.01982 -0.0801 0.9996 0.0110
-14.000 -1.1447 0.02259 0.01849 -0.0809 0.9976 0.0116
-13.750 -1.1197 0.02144 0.01726 -0.0818 0.9956 0.0125
-13.500 -1.0929 0.02048 0.01622 -0.0828 0.9941 0.0134
-13.250 -1.0674 0.01967 0.01532 -0.0833 0.9915 0.0142
-13.000 -1.0408 0.01887 0.01447 -0.0840 0.9891 0.0153
-12.750 -1.0128 0.01819 0.01372 -0.0848 0.9869 0.0165
-12.500 -0.9841 0.01758 0.01305 -0.0856 0.9849 0.0175
-12.250 -0.9571 0.01701 0.01242 -0.0860 0.9818 0.0183
-12.000 -0.9304 0.01651 0.01189 -0.0863 0.9780 0.0195
-11.750 -0.9018 0.01607 0.01142 -0.0868 0.9749 0.0206
-11.500 -0.8737 0.01566 0.01095 -0.0872 0.9717 0.0215
-11.250 -0.8477 0.01528 0.01049 -0.0871 0.9666 0.0221
-11.000 -0.8204 0.01488 0.01002 -0.0873 0.9622 0.0226
-10.750 -0.7946 0.01441 0.00952 -0.0872 0.9573 0.0234
-10.500 -0.7686 0.01406 0.00914 -0.0871 0.9515 0.0243
-10.250 -0.7419 0.01375 0.00878 -0.0870 0.9463 0.0251
-10.000 -0.7160 0.01345 0.00842 -0.0868 0.9403 0.0258
-9.750 -0.6899 0.01315 0.00806 -0.0865 0.9338 0.0264
-9.500 -0.6635 0.01287 0.00772 -0.0863 0.9278 0.0270
-9.250 -0.6371 0.01262 0.00740 -0.0861 0.9208 0.0274
-8.750 -0.5853 0.01191 0.00657 -0.0856 0.9066 0.0290
-8.500 -0.5589 0.01165 0.00627 -0.0853 0.8994 0.0299
-8.250 -0.5321 0.01141 0.00600 -0.0852 0.8918 0.0307
-8.000 -0.5055 0.01116 0.00568 -0.0850 0.8841 0.0313
-7.750 -0.4786 0.01093 0.00538 -0.0848 0.8761 0.0319
-7.500 -0.4517 0.01071 0.00510 -0.0846 0.8682 0.0326
-7.250 -0.4247 0.01049 0.00482 -0.0844 0.8596 0.0330
-7.000 -0.3977 0.01029 0.00455 -0.0843 0.8515 0.0334
-6.750 -0.3706 0.01008 0.00428 -0.0841 0.8427 0.0338
-6.500 -0.3437 0.00981 0.00395 -0.0839 0.8346 0.0350
-6.250 -0.3166 0.00961 0.00371 -0.0837 0.8258 0.0360
-6.000 -0.2892 0.00943 0.00349 -0.0836 0.8177 0.0370
-5.750 -0.2619 0.00928 0.00330 -0.0835 0.8090 0.0382
-5.500 -0.2343 0.00914 0.00312 -0.0834 0.8008 0.0394
-5.000 -0.1791 0.00889 0.00277 -0.0832 0.7839 0.0412
-4.750 -0.1517 0.00874 0.00257 -0.0831 0.7757 0.0435
-4.500 -0.1240 0.00860 0.00243 -0.0830 0.7673 0.0456
-4.250 -0.0963 0.00850 0.00229 -0.0829 0.7593 0.0476
-4.000 -0.0685 0.00841 0.00217 -0.0829 0.7509 0.0493
-3.750 -0.0407 0.00832 0.00204 -0.0828 0.7429 0.0515
-3.500 -0.0130 0.00821 0.00192 -0.0827 0.7344 0.0550
-3.250 0.0148 0.00813 0.00182 -0.0827 0.7264 0.0581
-3.000 0.0427 0.00807 0.00173 -0.0826 0.7174 0.0605
-2.750 0.0704 0.00798 0.00164 -0.0826 0.7088 0.0660
-2.250 0.1257 0.00788 0.00148 -0.0824 0.6875 0.0747
-2.000 0.1533 0.00782 0.00141 -0.0823 0.6767 0.0817
-1.750 0.1809 0.00777 0.00136 -0.0822 0.6664 0.0898
-1.500 0.2085 0.00769 0.00130 -0.0821 0.6565 0.1050
-1.250 0.2360 0.00760 0.00126 -0.0821 0.6469 0.1260
-0.750 0.2911 0.00748 0.00119 -0.0819 0.6264 0.1627
-0.500 0.3183 0.00738 0.00117 -0.0818 0.6160 0.1976
-0.250 0.3452 0.00727 0.00117 -0.0817 0.6048 0.2504
0.000 0.3727 0.00724 0.00118 -0.0816 0.5931 0.2755
0.250 0.4002 0.00724 0.00119 -0.0815 0.5812 0.2945
0.500 0.4274 0.00725 0.00121 -0.0814 0.5671 0.3155
0.750 0.4540 0.00726 0.00124 -0.0811 0.5485 0.3465
1.000 0.4798 0.00723 0.00129 -0.0808 0.5275 0.4053
1.250 0.5053 0.00706 0.00135 -0.0805 0.5096 0.5070
1.500 0.5304 0.00686 0.00142 -0.0801 0.4949 0.6212
1.750 0.5546 0.00666 0.00151 -0.0794 0.4797 0.7363
2.000 0.5793 0.00660 0.00161 -0.0787 0.4646 0.8063
2.250 0.6024 0.00654 0.00172 -0.0775 0.4509 0.8830
2.500 0.6282 0.00658 0.00183 -0.0768 0.4369 0.9409
2.750 0.6614 0.00673 0.00194 -0.0780 0.4214 0.9684
3.250 0.7296 0.00710 0.00215 -0.0809 0.3882 0.9931
3.500 0.7660 0.00731 0.00228 -0.0829 0.3690 0.9998
3.750 0.7904 0.00749 0.00240 -0.0822 0.3541 1.0000
4.000 0.8145 0.00768 0.00252 -0.0815 0.3410 1.0000
4.500 0.8635 0.00804 0.00279 -0.0802 0.3164 1.0000
4.750 0.8882 0.00823 0.00293 -0.0796 0.3045 1.0000
5.000 0.9124 0.00847 0.00310 -0.0790 0.2882 1.0000
5.250 0.9361 0.00876 0.00330 -0.0783 0.2688 1.0000
5.500 0.9599 0.00905 0.00350 -0.0776 0.2497 1.0000
5.750 0.9826 0.00944 0.00375 -0.0768 0.2237 1.0000
6.000 1.0058 0.00979 0.00400 -0.0760 0.2030 1.0000
6.250 1.0288 0.01014 0.00426 -0.0753 0.1839 1.0000
6.500 1.0521 0.01049 0.00452 -0.0745 0.1680 1.0000
6.750 1.0758 0.01080 0.00478 -0.0739 0.1557 1.0000
7.000 1.0988 0.01116 0.00507 -0.0731 0.1407 1.0000
7.250 1.1196 0.01168 0.00544 -0.0721 0.1148 1.0000
7.500 1.1373 0.01242 0.00597 -0.0706 0.0809 1.0000
7.750 1.1547 0.01318 0.00656 -0.0690 0.0514 1.0000
8.000 1.1730 0.01386 0.00712 -0.0675 0.0330 1.0000
8.250 1.1939 0.01431 0.00755 -0.0665 0.0269 1.0000
8.500 1.2152 0.01471 0.00795 -0.0655 0.0231 1.0000
8.750 1.2361 0.01513 0.00836 -0.0645 0.0201 1.0000
9.000 1.2563 0.01558 0.00880 -0.0634 0.0175 1.0000
9.250 1.2755 0.01599 0.00923 -0.0621 0.0158 1.0000
9.500 1.2939 0.01643 0.00968 -0.0606 0.0145 1.0000
9.750 1.3113 0.01692 0.01018 -0.0591 0.0133 1.0000
10.000 1.3289 0.01741 0.01070 -0.0576 0.0125 1.0000
10.250 1.3465 0.01790 0.01122 -0.0561 0.0119 1.0000
10.500 1.3633 0.01844 0.01180 -0.0547 0.0113 1.0000
10.750 1.3793 0.01903 0.01241 -0.0531 0.0107 1.0000
11.000 1.3942 0.01970 0.01311 -0.0515 0.0100 1.0000
11.250 1.4087 0.02041 0.01385 -0.0499 0.0096 1.0000
11.500 1.4239 0.02108 0.01457 -0.0484 0.0092 1.0000
11.750 1.4384 0.02181 0.01535 -0.0469 0.0089 1.0000
12.000 1.4520 0.02261 0.01620 -0.0454 0.0086 1.0000
12.250 1.4648 0.02349 0.01713 -0.0439 0.0083 1.0000
12.500 1.4768 0.02445 0.01813 -0.0424 0.0080 1.0000
12.750 1.4878 0.02551 0.01924 -0.0409 0.0077 1.0000
13.000 1.4971 0.02674 0.02052 -0.0394 0.0074 1.0000
13.250 1.5057 0.02805 0.02189 -0.0379 0.0072 1.0000
13.500 1.5155 0.02931 0.02322 -0.0366 0.0071 1.0000
13.750 1.5244 0.03068 0.02466 -0.0354 0.0069 1.0000
14.000 1.5324 0.03215 0.02621 -0.0343 0.0068 1.0000
14.250 1.5397 0.03373 0.02786 -0.0332 0.0066 1.0000
14.500 1.5461 0.03545 0.02965 -0.0322 0.0064 1.0000
14.750 1.5518 0.03728 0.03155 -0.0313 0.0063 1.0000
15.000 1.5563 0.03927 0.03360 -0.0305 0.0061 1.0000
15.250 1.5597 0.04142 0.03583 -0.0297 0.0060 1.0000
15.500 1.5619 0.04378 0.03827 -0.0291 0.0058 1.0000
15.750 1.5628 0.04635 0.04092 -0.0287 0.0057 1.0000
16.000 1.5623 0.04917 0.04382 -0.0284 0.0056 1.0000
16.250 1.5597 0.05235 0.04709 -0.0282 0.0055 1.0000
16.500 1.5553 0.05586 0.05070 -0.0283 0.0054 1.0000
16.750 1.5484 0.05978 0.05473 -0.0286 0.0053 1.0000
17.000 1.5440 0.06351 0.05856 -0.0291 0.0053 1.0000
17.250 1.5386 0.06747 0.06263 -0.0297 0.0052 1.0000
17.500 1.5319 0.07170 0.06697 -0.0306 0.0052 1.0000
17.750 1.5241 0.07616 0.07153 -0.0316 0.0051 1.0000
18.000 1.5143 0.08103 0.07652 -0.0328 0.0051 1.0000
18.250 1.5038 0.08609 0.08169 -0.0343 0.0051 1.0000
18.500 1.4920 0.09143 0.08714 -0.0359 0.0050 1.0000
18.750 1.4795 0.09696 0.09278 -0.0377 0.0050 1.0000
19.000 1.4659 0.10276 0.09870 -0.0398 0.0050 1.0000
19.250 1.4522 0.10869 0.10474 -0.0420 0.0049 1.0000
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