CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 100,000 Max Cl/Cd: 56.28 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkv-il-100000-n5.txt Download as CSV file: xf-clarkv-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK V AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4521 0.09358 0.08857 -0.0437 1.0000 0.0420
-9.250 -0.4668 0.08972 0.08480 -0.0435 1.0000 0.0419
-9.000 -0.4855 0.08585 0.08101 -0.0431 1.0000 0.0419
-8.750 -0.5092 0.08218 0.07745 -0.0423 1.0000 0.0418
-8.500 -0.5357 0.07800 0.07335 -0.0422 1.0000 0.0415
-8.250 -0.5557 0.06986 0.06518 -0.0473 0.9982 0.0414
-8.000 -0.5616 0.05778 0.05263 -0.0574 0.9904 0.0422
-7.750 -0.5582 0.04878 0.04286 -0.0627 0.9843 0.0434
-7.500 -0.5472 0.04299 0.03626 -0.0646 0.9785 0.0441
-7.250 -0.5229 0.04057 0.03369 -0.0662 0.9753 0.0456
-7.000 -0.4993 0.03912 0.03211 -0.0670 0.9709 0.0474
-6.750 -0.4755 0.03677 0.02938 -0.0679 0.9666 0.0492
-6.500 -0.4477 0.03407 0.02617 -0.0693 0.9635 0.0505
-6.250 -0.4223 0.03203 0.02365 -0.0697 0.9594 0.0523
-6.000 -0.3956 0.03049 0.02155 -0.0700 0.9547 0.0543
-5.750 -0.3657 0.02884 0.01979 -0.0712 0.9516 0.0558
-5.500 -0.3327 0.02762 0.01841 -0.0727 0.9492 0.0574
-5.250 -0.3085 0.02665 0.01730 -0.0723 0.9437 0.0589
-5.000 -0.2789 0.02577 0.01623 -0.0729 0.9395 0.0613
-4.750 -0.2455 0.02499 0.01524 -0.0742 0.9363 0.0647
-4.500 -0.2116 0.02406 0.01422 -0.0756 0.9338 0.0672
-4.250 -0.1897 0.02338 0.01355 -0.0747 0.9270 0.0696
-4.000 -0.1584 0.02273 0.01285 -0.0756 0.9230 0.0733
-3.750 -0.1239 0.02212 0.01214 -0.0770 0.9201 0.0783
-3.500 -0.0999 0.02159 0.01165 -0.0765 0.9138 0.0848
-3.250 -0.0698 0.02111 0.01115 -0.0772 0.9090 0.0957
-3.000 -0.0355 0.02055 0.01066 -0.0787 0.9058 0.1123
-2.750 -0.0098 0.02016 0.01034 -0.0784 0.8995 0.1369
-2.500 0.0198 0.01962 0.01003 -0.0791 0.8944 0.1854
-2.250 0.0533 0.01888 0.00983 -0.0807 0.8913 0.2991
-2.000 0.0781 0.01841 0.00978 -0.0803 0.8849 0.4111
-1.750 0.1067 0.01797 0.00967 -0.0805 0.8797 0.5084
-1.500 0.1391 0.01745 0.00953 -0.0810 0.8766 0.6169
-1.250 0.1590 0.01711 0.00964 -0.0786 0.8695 0.7481
-1.000 0.2073 0.01690 0.00970 -0.0814 0.8670 0.9320
-0.750 0.2657 0.01681 0.00946 -0.0877 0.8649 1.0000
-0.500 0.3020 0.01665 0.00914 -0.0893 0.8614 1.0000
-0.250 0.3212 0.01671 0.00910 -0.0877 0.8517 1.0000
0.000 0.3564 0.01656 0.00883 -0.0891 0.8475 1.0000
0.250 0.3780 0.01662 0.00881 -0.0879 0.8384 1.0000
0.500 0.4122 0.01647 0.00858 -0.0890 0.8334 1.0000
0.750 0.4360 0.01651 0.00855 -0.0882 0.8245 1.0000
1.000 0.4703 0.01632 0.00830 -0.0892 0.8185 1.0000
1.250 0.4953 0.01628 0.00820 -0.0884 0.8079 1.0000
1.500 0.5301 0.01602 0.00788 -0.0894 0.8000 1.0000
1.750 0.5572 0.01594 0.00777 -0.0889 0.7890 1.0000
2.000 0.5831 0.01592 0.00773 -0.0884 0.7781 1.0000
2.250 0.6164 0.01578 0.00755 -0.0891 0.7698 1.0000
2.500 0.6424 0.01579 0.00756 -0.0886 0.7583 1.0000
2.750 0.6684 0.01582 0.00758 -0.0880 0.7464 1.0000
3.000 0.6967 0.01580 0.00757 -0.0879 0.7346 1.0000
3.250 0.7257 0.01577 0.00753 -0.0879 0.7221 1.0000
3.500 0.7528 0.01576 0.00751 -0.0874 0.7069 1.0000
3.750 0.7785 0.01579 0.00753 -0.0867 0.6891 1.0000
4.000 0.8045 0.01583 0.00754 -0.0860 0.6703 1.0000
4.250 0.8308 0.01590 0.00759 -0.0855 0.6518 1.0000
4.500 0.8569 0.01601 0.00768 -0.0849 0.6334 1.0000
4.750 0.8800 0.01620 0.00786 -0.0838 0.6133 1.0000
5.000 0.9036 0.01640 0.00804 -0.0828 0.5923 1.0000
5.250 0.9270 0.01663 0.00825 -0.0818 0.5704 1.0000
5.500 0.9485 0.01691 0.00851 -0.0805 0.5466 1.0000
5.750 0.9697 0.01723 0.00878 -0.0791 0.5215 1.0000
6.000 0.9898 0.01760 0.00908 -0.0776 0.4951 1.0000
6.250 1.0083 0.01803 0.00945 -0.0758 0.4661 1.0000
6.500 1.0252 0.01853 0.00983 -0.0737 0.4347 1.0000
6.750 1.0407 0.01910 0.01027 -0.0715 0.4031 1.0000
7.000 1.0560 0.01971 0.01077 -0.0694 0.3741 1.0000
7.250 1.0716 0.02033 0.01134 -0.0673 0.3492 1.0000
7.500 1.0866 0.02100 0.01193 -0.0652 0.3276 1.0000
7.750 1.1014 0.02165 0.01256 -0.0631 0.3076 1.0000
8.000 1.1159 0.02233 0.01323 -0.0610 0.2885 1.0000
8.250 1.1300 0.02304 0.01394 -0.0589 0.2704 1.0000
8.500 1.1438 0.02379 0.01471 -0.0568 0.2535 1.0000
8.750 1.1572 0.02457 0.01549 -0.0547 0.2375 1.0000
9.000 1.1698 0.02540 0.01633 -0.0525 0.2217 1.0000
9.250 1.1816 0.02628 0.01721 -0.0504 0.2045 1.0000
9.500 1.1920 0.02723 0.01815 -0.0482 0.1849 1.0000
9.750 1.2005 0.02831 0.01916 -0.0458 0.1649 1.0000
10.000 1.2097 0.02942 0.02026 -0.0437 0.1454 1.0000
10.250 1.2201 0.03051 0.02138 -0.0418 0.1286 1.0000
10.500 1.2293 0.03171 0.02259 -0.0398 0.1123 1.0000
10.750 1.2365 0.03309 0.02395 -0.0378 0.0968 1.0000
11.000 1.2416 0.03468 0.02550 -0.0356 0.0826 1.0000
11.250 1.2454 0.03645 0.02725 -0.0335 0.0691 1.0000
11.500 1.2482 0.03836 0.02918 -0.0314 0.0576 1.0000
11.750 1.2500 0.04040 0.03131 -0.0294 0.0494 1.0000
12.000 1.2505 0.04261 0.03359 -0.0275 0.0440 1.0000
12.250 1.2495 0.04501 0.03605 -0.0257 0.0401 1.0000
12.500 1.2483 0.04751 0.03866 -0.0242 0.0371 1.0000
12.750 1.2473 0.05008 0.04137 -0.0228 0.0347 1.0000
13.000 1.2444 0.05292 0.04432 -0.0217 0.0331 1.0000
13.250 1.2389 0.05611 0.04761 -0.0208 0.0319 1.0000
13.500 1.2358 0.05920 0.05085 -0.0200 0.0308 1.0000
13.750 1.2331 0.06236 0.05420 -0.0195 0.0296 1.0000
14.000 1.2297 0.06570 0.05769 -0.0193 0.0284 1.0000
14.250 1.2256 0.06924 0.06137 -0.0193 0.0274 1.0000
14.500 1.2207 0.07301 0.06528 -0.0196 0.0265 1.0000
14.750 1.2148 0.07699 0.06936 -0.0201 0.0258 1.0000
15.000 1.2094 0.08097 0.07343 -0.0205 0.0252 1.0000
15.250 1.2059 0.08488 0.07755 -0.0211 0.0246 1.0000
15.500 1.2018 0.08896 0.08181 -0.0218 0.0242 1.0000
15.750 1.1970 0.09325 0.08629 -0.0227 0.0237 1.0000
16.000 1.1913 0.09778 0.09102 -0.0239 0.0233 1.0000
16.250 1.1846 0.10263 0.09605 -0.0255 0.0230 1.0000
16.500 1.1768 0.10785 0.10145 -0.0275 0.0226 1.0000
16.750 1.1679 0.11343 0.10722 -0.0300 0.0223 1.0000
17.000 1.1577 0.11943 0.11340 -0.0329 0.0221 1.0000
17.250 1.1465 0.12591 0.12007 -0.0363 0.0219 1.0000
17.500 1.1335 0.13306 0.12740 -0.0403 0.0217 1.0000
17.750 1.1181 0.14116 0.13569 -0.0451 0.0217 1.0000
18.000 1.0972 0.15122 0.14597 -0.0514 0.0218 1.0000
18.250 1.0587 0.16752 0.16252 -0.0617 0.0226 1.0000
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