CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 100,000 Max Cl/Cd: 47.56 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarym15-il-100000.txt Download as CSV file: xf-clarym15-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YM-15 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3523 0.10319 0.09832 -0.0331 1.0000 0.1651
-8.750 -0.4163 0.10297 0.09830 -0.0319 1.0000 0.1688
-8.500 -0.4759 0.10229 0.09781 -0.0296 1.0000 0.1693
-8.250 -0.4210 0.09778 0.09324 -0.0265 1.0000 0.1722
-8.000 -0.4194 0.09616 0.09165 -0.0235 1.0000 0.1746
-7.750 -0.4315 0.09469 0.09025 -0.0207 1.0000 0.1773
-7.500 -0.4572 0.09326 0.08892 -0.0180 1.0000 0.1804
-7.250 -0.5917 0.05963 0.05422 -0.0440 0.9886 0.1090
-7.000 -0.5683 0.05478 0.04922 -0.0469 0.9832 0.1057
-6.750 -0.5685 0.04423 0.03703 -0.0493 0.9756 0.0976
-6.500 -0.5374 0.04127 0.03394 -0.0518 0.9705 0.0994
-6.250 -0.5081 0.03936 0.03188 -0.0533 0.9643 0.1012
-6.000 -0.4777 0.03710 0.02924 -0.0548 0.9580 0.1025
-5.750 -0.4386 0.03502 0.02674 -0.0577 0.9538 0.1046
-5.500 -0.4149 0.03356 0.02494 -0.0574 0.9456 0.1071
-5.250 -0.3768 0.03203 0.02302 -0.0597 0.9405 0.1115
-5.000 -0.3463 0.03107 0.02208 -0.0607 0.9339 0.1163
-4.750 -0.3132 0.03011 0.02089 -0.0618 0.9272 0.1223
-4.500 -0.2711 0.02902 0.01986 -0.0647 0.9229 0.1317
-4.250 -0.2472 0.02835 0.01914 -0.0642 0.9144 0.1418
-4.000 -0.2102 0.02763 0.01847 -0.0661 0.9087 0.1574
-3.750 -0.1749 0.02714 0.01808 -0.0677 0.9029 0.1768
-3.500 -0.1487 0.02683 0.01784 -0.0677 0.8942 0.1969
-3.250 -0.1073 0.02636 0.01750 -0.0703 0.8896 0.2269
-3.000 -0.0865 0.02625 0.01746 -0.0693 0.8801 0.2557
-2.750 -0.0493 0.02567 0.01715 -0.0711 0.8743 0.3019
-2.500 -0.0195 0.02518 0.01694 -0.0715 0.8667 0.3537
-2.250 0.0137 0.02459 0.01663 -0.0723 0.8584 0.4106
-2.000 0.0652 0.02356 0.01598 -0.0757 0.8542 0.4914
-1.500 0.1288 0.02191 0.01540 -0.0741 0.8374 0.7292
-1.250 0.1520 0.02194 0.01573 -0.0712 0.8262 0.8553
-1.000 0.2456 0.02170 0.01538 -0.0809 0.8246 0.9565
-0.750 0.3746 0.02098 0.01439 -0.0988 0.8244 0.9931
-0.500 0.4335 0.02023 0.01345 -0.1044 0.8197 1.0000
-0.250 0.4426 0.02034 0.01348 -0.1015 0.8066 1.0000
0.000 0.4649 0.02016 0.01318 -0.1003 0.7974 1.0000
0.250 0.4881 0.01995 0.01287 -0.0993 0.7876 1.0000
0.500 0.5055 0.01996 0.01279 -0.0973 0.7763 1.0000
0.750 0.5376 0.01952 0.01222 -0.0974 0.7684 1.0000
1.000 0.5531 0.01961 0.01225 -0.0950 0.7557 1.0000
1.250 0.5829 0.01929 0.01183 -0.0947 0.7470 1.0000
1.500 0.6046 0.01923 0.01169 -0.0932 0.7352 1.0000
1.750 0.6248 0.01923 0.01163 -0.0915 0.7228 1.0000
2.000 0.6564 0.01889 0.01117 -0.0914 0.7130 1.0000
2.250 0.6789 0.01881 0.01101 -0.0899 0.6995 1.0000
2.500 0.7001 0.01879 0.01094 -0.0883 0.6852 1.0000
2.750 0.7237 0.01873 0.01080 -0.0870 0.6710 1.0000
3.000 0.7489 0.01866 0.01064 -0.0859 0.6568 1.0000
3.250 0.7746 0.01859 0.01046 -0.0850 0.6419 1.0000
3.500 0.7994 0.01858 0.01033 -0.0839 0.6260 1.0000
3.750 0.8230 0.01864 0.01029 -0.0827 0.6092 1.0000
4.000 0.8464 0.01877 0.01030 -0.0815 0.5924 1.0000
4.250 0.8706 0.01896 0.01036 -0.0805 0.5765 1.0000
4.500 0.8921 0.01927 0.01059 -0.0792 0.5606 1.0000
4.750 0.9132 0.01963 0.01088 -0.0779 0.5455 1.0000
5.000 0.9347 0.02003 0.01122 -0.0766 0.5318 1.0000
5.250 0.9587 0.02043 0.01155 -0.0759 0.5200 1.0000
5.500 0.9843 0.02081 0.01182 -0.0754 0.5092 1.0000
5.750 1.0039 0.02133 0.01238 -0.0740 0.4980 1.0000
6.000 1.0304 0.02175 0.01269 -0.0737 0.4888 1.0000
6.250 1.0504 0.02226 0.01324 -0.0724 0.4786 1.0000
6.500 1.0742 0.02275 0.01369 -0.0717 0.4696 1.0000
6.750 1.0965 0.02321 0.01416 -0.0708 0.4602 1.0000
7.000 1.1184 0.02374 0.01470 -0.0698 0.4513 1.0000
7.250 1.1422 0.02414 0.01506 -0.0691 0.4420 1.0000
7.500 1.1608 0.02468 0.01565 -0.0677 0.4323 1.0000
7.750 1.1889 0.02500 0.01583 -0.0676 0.4229 1.0000
8.000 1.2027 0.02559 0.01658 -0.0654 0.4131 1.0000
8.250 1.2292 0.02602 0.01690 -0.0652 0.4043 1.0000
8.500 1.2447 0.02662 0.01765 -0.0633 0.3951 1.0000
8.750 1.2693 0.02714 0.01811 -0.0629 0.3865 1.0000
9.000 1.2858 0.02773 0.01880 -0.0612 0.3772 1.0000
9.250 1.3072 0.02834 0.01942 -0.0603 0.3683 1.0000
9.500 1.3262 0.02889 0.01999 -0.0590 0.3586 1.0000
9.750 1.3419 0.02961 0.02080 -0.0572 0.3491 1.0000
10.000 1.3682 0.03010 0.02116 -0.0570 0.3389 1.0000
10.250 1.3740 0.03092 0.02221 -0.0538 0.3288 1.0000
10.500 1.3937 0.03155 0.02279 -0.0527 0.3182 1.0000
10.750 1.4069 0.03216 0.02344 -0.0506 0.3071 1.0000
11.000 1.4122 0.03303 0.02445 -0.0475 0.2962 1.0000
11.250 1.4279 0.03367 0.02503 -0.0458 0.2850 1.0000
11.500 1.4311 0.03439 0.02583 -0.0423 0.2742 1.0000
11.750 1.4302 0.03537 0.02691 -0.0385 0.2640 1.0000
12.000 1.4422 0.03601 0.02745 -0.0364 0.2536 1.0000
12.250 1.4367 0.03720 0.02882 -0.0324 0.2440 1.0000
12.500 1.4408 0.03832 0.02997 -0.0299 0.2351 1.0000
12.750 1.4468 0.03935 0.03099 -0.0276 0.2264 1.0000
13.000 1.4464 0.04094 0.03271 -0.0250 0.2187 1.0000
13.250 1.4561 0.04199 0.03371 -0.0234 0.2112 1.0000
13.500 1.4563 0.04381 0.03566 -0.0212 0.2047 1.0000
13.750 1.4624 0.04528 0.03719 -0.0196 0.1984 1.0000
14.000 1.4760 0.04665 0.03852 -0.0185 0.1928 1.0000
14.250 1.4708 0.04903 0.04114 -0.0165 0.1881 1.0000
14.500 1.4854 0.05018 0.04224 -0.0156 0.1827 1.0000
14.750 1.4914 0.05212 0.04426 -0.0144 0.1781 1.0000
15.000 1.4800 0.05507 0.04747 -0.0126 0.1744 1.0000
15.250 1.4888 0.05656 0.04896 -0.0117 0.1695 1.0000
15.500 1.5015 0.05809 0.05045 -0.0110 0.1647 1.0000
15.750 1.4813 0.06196 0.05464 -0.0095 0.1620 1.0000
16.000 1.4686 0.06540 0.05827 -0.0086 0.1587 1.0000
16.250 1.5051 0.06464 0.05721 -0.0083 0.1518 1.0000
16.500 1.4775 0.06946 0.06237 -0.0075 0.1500 1.0000
16.750 1.4494 0.07483 0.06804 -0.0074 0.1481 1.0000
17.000 1.4205 0.08081 0.07429 -0.0080 0.1463 1.0000
17.250 1.3901 0.08750 0.08121 -0.0094 0.1445 1.0000
17.500 1.3600 0.09464 0.08855 -0.0114 0.1427 1.0000
17.750 1.3267 0.10282 0.09690 -0.0143 0.1411 1.0000
18.000 1.2904 0.11216 0.10639 -0.0181 0.1396 1.0000
18.500 1.3737 0.10427 0.09828 -0.0131 0.1262 1.0000
18.750 0.9207 0.21962 0.21379 -0.0820 0.1834 1.0000
19.000 0.9367 0.22378 0.21801 -0.0820 0.1794 1.0000
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