CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 50,000 Max Cl/Cd: 36.38 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkx-il-50000-n5.txt Download as CSV file: xf-clarkx-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4142 0.11311 0.10550 -0.0414 1.0000 0.0860
-10.250 -0.4151 0.10912 0.10155 -0.0428 1.0000 0.0860
-10.000 -0.4195 0.10497 0.09746 -0.0447 1.0000 0.0862
-9.750 -0.4236 0.10088 0.09344 -0.0462 1.0000 0.0862
-9.500 -0.4261 0.09706 0.08967 -0.0470 1.0000 0.0860
-9.250 -0.4277 0.09354 0.08619 -0.0471 1.0000 0.0857
-9.000 -0.4328 0.09008 0.08281 -0.0472 1.0000 0.0852
-8.750 -0.4431 0.08668 0.07951 -0.0470 1.0000 0.0848
-8.500 -0.4575 0.08320 0.07614 -0.0470 1.0000 0.0843
-8.250 -0.4713 0.07920 0.07224 -0.0474 1.0000 0.0839
-8.000 -0.4866 0.07502 0.06809 -0.0477 1.0000 0.0837
-7.750 -0.5025 0.07062 0.06367 -0.0477 1.0000 0.0837
-7.500 -0.5172 0.06607 0.05901 -0.0477 1.0000 0.0841
-7.250 -0.5291 0.06133 0.05404 -0.0478 1.0000 0.0848
-7.000 -0.5359 0.05661 0.04895 -0.0477 1.0000 0.0856
-6.750 -0.5357 0.05239 0.04427 -0.0474 1.0000 0.0862
-6.500 -0.5275 0.04951 0.04123 -0.0465 1.0000 0.0870
-6.250 -0.5168 0.04694 0.03841 -0.0457 1.0000 0.0878
-6.000 -0.5040 0.04462 0.03586 -0.0449 1.0000 0.0889
-5.750 -0.4833 0.04243 0.03341 -0.0455 0.9979 0.0909
-5.500 -0.4515 0.04007 0.03062 -0.0481 0.9924 0.0950
-5.250 -0.4189 0.03743 0.02733 -0.0506 0.9868 0.0985
-5.000 -0.3855 0.03522 0.02458 -0.0527 0.9814 0.1009
-4.750 -0.3524 0.03380 0.02302 -0.0546 0.9757 0.1039
-4.500 -0.3190 0.03268 0.02168 -0.0563 0.9698 0.1094
-4.250 -0.2847 0.03147 0.02003 -0.0580 0.9636 0.1153
-4.000 -0.2507 0.03047 0.01900 -0.0597 0.9580 0.1201
-3.750 -0.2182 0.02964 0.01795 -0.0609 0.9511 0.1272
-3.500 -0.1809 0.02888 0.01714 -0.0631 0.9460 0.1367
-3.250 -0.1515 0.02823 0.01630 -0.0635 0.9380 0.1458
-3.000 -0.1149 0.02758 0.01565 -0.0655 0.9324 0.1593
-2.750 -0.0847 0.02706 0.01511 -0.0663 0.9247 0.1761
-2.500 -0.0499 0.02649 0.01468 -0.0679 0.9182 0.1986
-2.250 -0.0177 0.02603 0.01437 -0.0691 0.9110 0.2381
-2.000 0.0144 0.02553 0.01413 -0.0703 0.9036 0.2998
-1.750 0.0471 0.02491 0.01393 -0.0716 0.8971 0.3874
-1.500 0.0733 0.02428 0.01388 -0.0713 0.8888 0.5050
-1.250 0.1031 0.02338 0.01399 -0.0699 0.8842 0.7446
-1.000 0.1597 0.02324 0.01389 -0.0748 0.8767 1.0000
-0.750 0.1974 0.02331 0.01366 -0.0768 0.8699 1.0000
-0.500 0.2217 0.02351 0.01363 -0.0764 0.8592 1.0000
-0.250 0.2553 0.02360 0.01351 -0.0776 0.8516 1.0000
0.250 0.3099 0.02394 0.01353 -0.0776 0.8318 1.0000
0.500 0.3448 0.02396 0.01340 -0.0787 0.8243 1.0000
0.750 0.3684 0.02419 0.01353 -0.0780 0.8129 1.0000
1.000 0.3982 0.02429 0.01352 -0.0782 0.8038 1.0000
1.250 0.4287 0.02434 0.01349 -0.0784 0.7944 1.0000
1.500 0.4532 0.02454 0.01363 -0.0777 0.7829 1.0000
1.750 0.4842 0.02455 0.01358 -0.0779 0.7738 1.0000
2.000 0.5126 0.02461 0.01359 -0.0777 0.7633 1.0000
2.250 0.5369 0.02480 0.01376 -0.0769 0.7513 1.0000
2.500 0.5652 0.02486 0.01380 -0.0766 0.7408 1.0000
2.750 0.5962 0.02481 0.01373 -0.0766 0.7310 1.0000
3.000 0.6196 0.02502 0.01395 -0.0757 0.7182 1.0000
3.250 0.6449 0.02517 0.01410 -0.0749 0.7059 1.0000
3.500 0.6729 0.02520 0.01415 -0.0744 0.6944 1.0000
3.750 0.7037 0.02509 0.01405 -0.0742 0.6834 1.0000
4.000 0.7274 0.02526 0.01426 -0.0732 0.6694 1.0000
4.250 0.7518 0.02541 0.01446 -0.0722 0.6552 1.0000
4.500 0.7766 0.02552 0.01460 -0.0712 0.6406 1.0000
4.750 0.8015 0.02561 0.01474 -0.0702 0.6255 1.0000
5.000 0.8265 0.02570 0.01489 -0.0692 0.6098 1.0000
5.250 0.8513 0.02580 0.01502 -0.0682 0.5937 1.0000
5.500 0.8759 0.02592 0.01518 -0.0671 0.5772 1.0000
5.750 0.9005 0.02607 0.01538 -0.0661 0.5605 1.0000
6.000 0.9247 0.02627 0.01561 -0.0650 0.5435 1.0000
6.250 0.9458 0.02665 0.01605 -0.0637 0.5255 1.0000
6.500 0.9675 0.02704 0.01651 -0.0624 0.5079 1.0000
6.750 0.9892 0.02745 0.01700 -0.0612 0.4902 1.0000
7.000 1.0109 0.02790 0.01751 -0.0600 0.4729 1.0000
7.250 1.0325 0.02840 0.01806 -0.0588 0.4558 1.0000
7.750 1.0747 0.02954 0.01936 -0.0563 0.4230 1.0000
8.000 1.0951 0.03020 0.02010 -0.0551 0.4072 1.0000
8.250 1.1150 0.03093 0.02091 -0.0538 0.3919 1.0000
8.500 1.1343 0.03172 0.02181 -0.0526 0.3772 1.0000
8.750 1.1529 0.03256 0.02279 -0.0512 0.3628 1.0000
9.000 1.1696 0.03340 0.02373 -0.0496 0.3475 1.0000
9.250 1.1824 0.03418 0.02455 -0.0474 0.3300 1.0000
9.500 1.1877 0.03504 0.02542 -0.0444 0.3099 1.0000
9.750 1.1861 0.03606 0.02649 -0.0406 0.2892 1.0000
10.000 1.1839 0.03722 0.02761 -0.0371 0.2685 1.0000
10.250 1.1821 0.03868 0.02913 -0.0342 0.2482 1.0000
10.500 1.1817 0.04031 0.03085 -0.0318 0.2290 1.0000
10.750 1.1804 0.04216 0.03273 -0.0297 0.2097 1.0000
11.000 1.1774 0.04435 0.03497 -0.0278 0.1884 1.0000
11.250 1.1724 0.04692 0.03755 -0.0263 0.1660 1.0000
11.500 1.1662 0.04992 0.04055 -0.0251 0.1415 1.0000
11.750 1.1580 0.05334 0.04388 -0.0242 0.1194 1.0000
12.000 1.1494 0.05703 0.04749 -0.0236 0.1030 1.0000
12.250 1.1406 0.06091 0.05129 -0.0233 0.0922 1.0000
12.500 1.1314 0.06497 0.05528 -0.0232 0.0849 1.0000
12.750 1.1258 0.06878 0.05915 -0.0231 0.0780 1.0000
13.000 1.1189 0.07277 0.06313 -0.0232 0.0734 1.0000
13.250 1.1154 0.07645 0.06690 -0.0231 0.0693 1.0000
13.500 1.1128 0.08009 0.07070 -0.0232 0.0655 1.0000
13.750 1.1097 0.08380 0.07445 -0.0235 0.0624 1.0000
14.000 1.1079 0.08742 0.07813 -0.0237 0.0596 1.0000
14.250 1.1070 0.09116 0.08210 -0.0241 0.0569 1.0000
14.500 1.1062 0.09486 0.08595 -0.0245 0.0547 1.0000
14.750 1.1065 0.09839 0.08958 -0.0249 0.0529 1.0000
15.000 1.1087 0.10148 0.09269 -0.0250 0.0511 1.0000
15.250 1.1067 0.10569 0.09707 -0.0259 0.0498 1.0000
15.500 1.0996 0.11111 0.10278 -0.0278 0.0487 1.0000
15.750 1.0904 0.11713 0.10907 -0.0304 0.0478 1.0000
16.000 1.0787 0.12392 0.11610 -0.0337 0.0472 1.0000
16.250 1.0635 0.13186 0.12427 -0.0380 0.0468 1.0000
16.500 1.0420 0.14201 0.13467 -0.0439 0.0470 1.0000
16.750 1.0136 0.15525 0.14807 -0.0519 0.0477 1.0000
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