CLARK YM-18 AIRFOIL (clarym18-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YM-18 AIRFOIL (clarym18-il) Reynolds number: 200,000 Max Cl/Cd: 60.86 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarym18-il-200000.txt Download as CSV file: xf-clarym18-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YM-18 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6984 0.06438 0.05960 -0.0919 1.0000 0.0638
-13.250 -0.7367 0.06017 0.05529 -0.0910 1.0000 0.0636
-13.000 -0.7747 0.05726 0.05231 -0.0878 1.0000 0.0634
-12.750 -0.8129 0.05524 0.05022 -0.0830 1.0000 0.0633
-12.500 -0.8508 0.05385 0.04876 -0.0769 1.0000 0.0632
-12.250 -0.8873 0.05251 0.04733 -0.0705 0.9991 0.0631
-12.000 -0.8954 0.04793 0.04224 -0.0719 0.9922 0.0635
-11.750 -0.8913 0.04434 0.03823 -0.0724 0.9845 0.0640
-11.500 -0.8646 0.04202 0.03585 -0.0745 0.9812 0.0648
-11.250 -0.8415 0.04039 0.03415 -0.0754 0.9761 0.0656
-11.000 -0.8170 0.03881 0.03245 -0.0765 0.9708 0.0665
-10.750 -0.7894 0.03693 0.03036 -0.0782 0.9673 0.0677
-10.500 -0.7724 0.03532 0.02849 -0.0778 0.9602 0.0689
-10.250 -0.7498 0.03366 0.02643 -0.0783 0.9548 0.0704
-10.000 -0.7157 0.03196 0.02468 -0.0805 0.9522 0.0720
-9.750 -0.6911 0.03105 0.02375 -0.0806 0.9460 0.0734
-9.500 -0.6626 0.03000 0.02260 -0.0813 0.9408 0.0752
-9.250 -0.6286 0.02879 0.02115 -0.0831 0.9375 0.0774
-9.000 -0.5902 0.02740 0.01969 -0.0857 0.9356 0.0799
-8.750 -0.5691 0.02679 0.01912 -0.0848 0.9279 0.0820
-8.500 -0.5363 0.02598 0.01817 -0.0860 0.9235 0.0854
-8.250 -0.4992 0.02483 0.01699 -0.0882 0.9209 0.0889
-8.000 -0.4610 0.02398 0.01616 -0.0904 0.9187 0.0930
-7.750 -0.4419 0.02350 0.01552 -0.0888 0.9104 0.0965
-7.500 -0.4110 0.02262 0.01478 -0.0896 0.9057 0.1011
-7.250 -0.3764 0.02197 0.01399 -0.0908 0.9024 0.1068
-7.000 -0.3410 0.02107 0.01321 -0.0924 0.8999 0.1126
-6.750 -0.3256 0.02086 0.01290 -0.0901 0.8899 0.1173
-6.500 -0.2952 0.02008 0.01224 -0.0906 0.8856 0.1235
-6.250 -0.2615 0.01949 0.01158 -0.0916 0.8824 0.1307
-6.000 -0.2436 0.01913 0.01131 -0.0898 0.8735 0.1367
-5.750 -0.2153 0.01865 0.01080 -0.0897 0.8681 0.1448
-5.500 -0.1842 0.01811 0.01030 -0.0902 0.8643 0.1545
-5.250 -0.1637 0.01779 0.01006 -0.0889 0.8564 0.1639
-5.000 -0.1378 0.01737 0.00969 -0.0884 0.8500 0.1769
-4.750 -0.1072 0.01684 0.00922 -0.0886 0.8454 0.1947
-4.500 -0.0864 0.01659 0.00907 -0.0872 0.8367 0.2147
-4.250 -0.0592 0.01624 0.00873 -0.0868 0.8298 0.2406
-4.000 -0.0282 0.01581 0.00837 -0.0870 0.8246 0.2657
-3.750 -0.0083 0.01570 0.00830 -0.0854 0.8144 0.2852
-3.500 0.0213 0.01538 0.00798 -0.0854 0.8084 0.3054
-3.250 0.0459 0.01521 0.00783 -0.0846 0.8005 0.3232
-3.000 0.0720 0.01498 0.00761 -0.0840 0.7925 0.3412
-2.500 0.1240 0.01451 0.00719 -0.0828 0.7763 0.3790
-2.250 0.1528 0.01416 0.00688 -0.0827 0.7693 0.4013
-2.000 0.1754 0.01396 0.00682 -0.0815 0.7605 0.4258
-1.750 0.2011 0.01370 0.00667 -0.0809 0.7531 0.4590
-1.500 0.2268 0.01340 0.00654 -0.0803 0.7467 0.5044
-1.250 0.2467 0.01313 0.00657 -0.0785 0.7377 0.5670
-1.000 0.2708 0.01278 0.00651 -0.0772 0.7310 0.6506
-0.750 0.2914 0.01264 0.00665 -0.0751 0.7222 0.7254
-0.500 0.3171 0.01255 0.00669 -0.0738 0.7141 0.7814
-0.250 0.3436 0.01258 0.00677 -0.0728 0.7060 0.8231
0.000 0.3703 0.01265 0.00686 -0.0718 0.6970 0.8563
0.250 0.4028 0.01277 0.00691 -0.0719 0.6894 0.8825
0.500 0.4324 0.01292 0.00705 -0.0716 0.6794 0.9048
0.750 0.4703 0.01306 0.00707 -0.0729 0.6711 0.9218
1.000 0.5065 0.01322 0.00720 -0.0741 0.6598 0.9366
1.250 0.5466 0.01335 0.00722 -0.0761 0.6494 0.9495
1.500 0.5964 0.01344 0.00721 -0.0803 0.6368 0.9577
1.750 0.6398 0.01354 0.00725 -0.0833 0.6235 0.9676
2.000 0.6846 0.01362 0.00722 -0.0867 0.6101 0.9772
2.250 0.7321 0.01366 0.00713 -0.0907 0.5951 0.9845
2.500 0.7768 0.01374 0.00709 -0.0942 0.5784 0.9930
2.750 0.8236 0.01380 0.00702 -0.0983 0.5589 1.0000
3.000 0.8386 0.01390 0.00703 -0.0962 0.5416 1.0000
3.250 0.8527 0.01405 0.00707 -0.0938 0.5237 1.0000
3.500 0.8660 0.01423 0.00715 -0.0913 0.5061 1.0000
3.750 0.8790 0.01445 0.00726 -0.0886 0.4897 1.0000
4.000 0.8918 0.01469 0.00740 -0.0859 0.4748 1.0000
4.250 0.9050 0.01496 0.00755 -0.0833 0.4621 1.0000
4.500 0.9183 0.01524 0.00772 -0.0807 0.4506 1.0000
4.750 0.9321 0.01550 0.00793 -0.0781 0.4400 1.0000
5.000 0.9472 0.01582 0.00811 -0.0758 0.4312 1.0000
5.250 0.9626 0.01609 0.00837 -0.0736 0.4231 1.0000
5.500 0.9792 0.01640 0.00860 -0.0715 0.4159 1.0000
5.750 0.9979 0.01675 0.00886 -0.0699 0.4094 1.0000
6.000 1.0141 0.01703 0.00914 -0.0678 0.4027 1.0000
6.250 1.0333 0.01737 0.00941 -0.0663 0.3968 1.0000
6.500 1.0539 0.01775 0.00973 -0.0652 0.3911 1.0000
6.750 1.0712 0.01806 0.01006 -0.0633 0.3853 1.0000
7.000 1.0913 0.01841 0.01038 -0.0621 0.3800 1.0000
7.250 1.1177 0.01890 0.01074 -0.0620 0.3749 1.0000
7.500 1.1339 0.01922 0.01115 -0.0601 0.3700 1.0000
7.750 1.1527 0.01957 0.01151 -0.0586 0.3645 1.0000
8.000 1.1771 0.02003 0.01185 -0.0583 0.3587 1.0000
8.250 1.1932 0.02042 0.01230 -0.0564 0.3532 1.0000
8.500 1.2075 0.02076 0.01267 -0.0541 0.3473 1.0000
8.750 1.2287 0.02118 0.01302 -0.0533 0.3416 1.0000
9.000 1.2485 0.02167 0.01352 -0.0522 0.3367 1.0000
9.250 1.2622 0.02207 0.01401 -0.0499 0.3321 1.0000
9.500 1.2799 0.02249 0.01445 -0.0485 0.3273 1.0000
9.750 1.3058 0.02300 0.01487 -0.0485 0.3225 1.0000
10.000 1.3209 0.02352 0.01548 -0.0468 0.3182 1.0000
10.250 1.3327 0.02400 0.01605 -0.0445 0.3135 1.0000
10.500 1.3486 0.02447 0.01654 -0.0429 0.3086 1.0000
10.750 1.3762 0.02503 0.01698 -0.0433 0.3032 1.0000
11.000 1.3798 0.02561 0.01775 -0.0399 0.2988 1.0000
11.250 1.3899 0.02619 0.01842 -0.0377 0.2937 1.0000
11.500 1.4048 0.02673 0.01895 -0.0362 0.2888 1.0000
11.750 1.4203 0.02739 0.01962 -0.0349 0.2837 1.0000
12.000 1.4243 0.02818 0.02057 -0.0322 0.2783 1.0000
12.250 1.4333 0.02889 0.02132 -0.0302 0.2729 1.0000
12.500 1.4468 0.02960 0.02200 -0.0288 0.2674 1.0000
12.750 1.4472 0.03071 0.02329 -0.0262 0.2613 1.0000
13.000 1.4533 0.03167 0.02428 -0.0243 0.2554 1.0000
13.250 1.4598 0.03276 0.02542 -0.0226 0.2492 1.0000
13.500 1.4610 0.03414 0.02694 -0.0206 0.2422 1.0000
13.750 1.4675 0.03532 0.02804 -0.0192 0.2358 1.0000
14.000 1.4659 0.03714 0.03006 -0.0175 0.2277 1.0000
14.250 1.4685 0.03872 0.03156 -0.0160 0.2205 1.0000
14.500 1.4666 0.04086 0.03387 -0.0147 0.2114 1.0000
14.750 1.4659 0.04298 0.03596 -0.0136 0.2034 1.0000
15.000 1.4639 0.04538 0.03841 -0.0126 0.1947 1.0000
15.250 1.4620 0.04786 0.04089 -0.0117 0.1869 1.0000
15.500 1.4597 0.05045 0.04345 -0.0109 0.1797 1.0000
15.750 1.4583 0.05306 0.04609 -0.0102 0.1730 1.0000
16.000 1.4572 0.05567 0.04871 -0.0097 0.1671 1.0000
16.250 1.4586 0.05801 0.05100 -0.0090 0.1620 1.0000
16.500 1.4576 0.06079 0.05388 -0.0087 0.1571 1.0000
16.750 1.4600 0.06310 0.05615 -0.0083 0.1529 1.0000
17.000 1.4646 0.06518 0.05822 -0.0079 0.1490 1.0000
17.250 1.4643 0.06800 0.06117 -0.0078 0.1456 1.0000
17.500 1.4665 0.07049 0.06371 -0.0077 0.1425 1.0000
17.750 1.4748 0.07213 0.06528 -0.0073 0.1395 1.0000
18.000 1.4801 0.07422 0.06741 -0.0070 0.1368 1.0000
18.250 1.4762 0.07763 0.07098 -0.0074 0.1343 1.0000
18.500 1.4755 0.08061 0.07405 -0.0077 0.1316 1.0000
18.750 1.4788 0.08301 0.07648 -0.0079 0.1291 1.0000
19.000 1.4958 0.08342 0.07674 -0.0071 0.1261 1.0000
19.250 1.4853 0.08783 0.08138 -0.0082 0.1244 1.0000
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Polar data table (+)
Polar graphs
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