CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 500,000 Max Cl/Cd: 88.9 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarym15-il-500000.txt Download as CSV file: xf-clarym15-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7444 0.05630 0.05302 -0.0877 1.0000 0.0340
-13.500 -0.7818 0.04841 0.04490 -0.0939 1.0000 0.0338
-13.250 -0.8119 0.04414 0.04046 -0.0944 1.0000 0.0338
-13.000 -0.8428 0.04177 0.03797 -0.0907 1.0000 0.0338
-12.750 -0.8789 0.04068 0.03682 -0.0835 1.0000 0.0338
-12.500 -0.8919 0.03844 0.03437 -0.0809 0.9972 0.0339
-12.250 -0.8760 0.03550 0.03109 -0.0834 0.9935 0.0343
-12.000 -0.8586 0.03359 0.02889 -0.0844 0.9887 0.0346
-11.750 -0.8405 0.03078 0.02579 -0.0858 0.9850 0.0351
-11.500 -0.8147 0.02859 0.02349 -0.0874 0.9829 0.0355
-11.250 -0.7849 0.02716 0.02198 -0.0892 0.9813 0.0359
-11.000 -0.7611 0.02602 0.02075 -0.0895 0.9761 0.0364
-10.750 -0.7312 0.02485 0.01947 -0.0909 0.9733 0.0368
-10.500 -0.6991 0.02372 0.01823 -0.0927 0.9714 0.0374
-10.250 -0.6667 0.02270 0.01710 -0.0944 0.9695 0.0381
-10.000 -0.6402 0.02181 0.01609 -0.0947 0.9647 0.0386
-9.750 -0.6132 0.02091 0.01508 -0.0949 0.9598 0.0391
-9.500 -0.5833 0.02008 0.01412 -0.0957 0.9562 0.0395
-9.250 -0.5577 0.01926 0.01320 -0.0955 0.9509 0.0399
-9.000 -0.5355 0.01809 0.01199 -0.0949 0.9440 0.0406
-8.750 -0.5093 0.01732 0.01119 -0.0947 0.9392 0.0412
-8.500 -0.4868 0.01677 0.01062 -0.0938 0.9314 0.0418
-8.250 -0.4619 0.01624 0.01004 -0.0933 0.9250 0.0426
-8.000 -0.4373 0.01576 0.00951 -0.0926 0.9184 0.0435
-7.750 -0.4131 0.01530 0.00898 -0.0919 0.9108 0.0443
-7.500 -0.3871 0.01484 0.00844 -0.0915 0.9051 0.0450
-7.250 -0.3639 0.01431 0.00786 -0.0906 0.8968 0.0458
-7.000 -0.3397 0.01373 0.00726 -0.0899 0.8902 0.0470
-6.750 -0.3146 0.01335 0.00686 -0.0894 0.8828 0.0482
-6.500 -0.2890 0.01301 0.00648 -0.0889 0.8755 0.0496
-6.250 -0.2625 0.01271 0.00611 -0.0885 0.8691 0.0511
-6.000 -0.2377 0.01230 0.00569 -0.0879 0.8612 0.0533
-5.750 -0.2109 0.01202 0.00538 -0.0876 0.8547 0.0561
-5.500 -0.1851 0.01175 0.00508 -0.0871 0.8465 0.0595
-5.250 -0.1587 0.01146 0.00478 -0.0867 0.8388 0.0647
-5.000 -0.1327 0.01117 0.00452 -0.0862 0.8303 0.0727
-4.750 -0.1062 0.01093 0.00427 -0.0858 0.8219 0.0829
-4.500 -0.0796 0.01071 0.00406 -0.0855 0.8141 0.0926
-4.250 -0.0528 0.01053 0.00386 -0.0852 0.8063 0.1016
-4.000 -0.0256 0.01039 0.00369 -0.0850 0.7986 0.1100
-3.750 0.0007 0.01016 0.00350 -0.0846 0.7898 0.1209
-3.500 0.0276 0.00997 0.00332 -0.0843 0.7822 0.1341
-3.250 0.0539 0.00975 0.00318 -0.0840 0.7737 0.1550
-3.000 0.0805 0.00955 0.00306 -0.0837 0.7662 0.1885
-2.750 0.1069 0.00936 0.00298 -0.0833 0.7571 0.2209
-2.500 0.1337 0.00923 0.00288 -0.0830 0.7485 0.2506
-2.250 0.1602 0.00909 0.00282 -0.0827 0.7387 0.2772
-2.000 0.1870 0.00897 0.00274 -0.0824 0.7305 0.3049
-1.750 0.2137 0.00883 0.00269 -0.0821 0.7218 0.3329
-1.250 0.2663 0.00852 0.00258 -0.0814 0.7050 0.4076
-1.000 0.2918 0.00833 0.00253 -0.0809 0.6969 0.4677
-0.750 0.3166 0.00808 0.00252 -0.0803 0.6874 0.5391
-0.500 0.3406 0.00785 0.00251 -0.0794 0.6785 0.6206
-0.250 0.3640 0.00761 0.00254 -0.0783 0.6684 0.7041
0.000 0.3873 0.00746 0.00260 -0.0770 0.6590 0.7805
0.250 0.4113 0.00738 0.00268 -0.0757 0.6491 0.8429
0.500 0.4369 0.00740 0.00278 -0.0747 0.6393 0.8911
0.750 0.4648 0.00751 0.00287 -0.0743 0.6289 0.9256
1.000 0.4954 0.00762 0.00296 -0.0745 0.6178 0.9483
1.250 0.5296 0.00777 0.00303 -0.0756 0.6063 0.9617
1.500 0.5651 0.00792 0.00309 -0.0771 0.5934 0.9712
1.750 0.6030 0.00806 0.00316 -0.0792 0.5789 0.9786
2.000 0.6440 0.00821 0.00322 -0.0820 0.5635 0.9840
2.250 0.6841 0.00837 0.00329 -0.0846 0.5475 0.9893
2.500 0.7231 0.00854 0.00337 -0.0871 0.5300 0.9942
2.750 0.7637 0.00873 0.00344 -0.0899 0.5101 0.9984
3.000 0.7911 0.00892 0.00353 -0.0900 0.4900 1.0000
3.250 0.8099 0.00911 0.00362 -0.0883 0.4685 1.0000
3.500 0.8276 0.00935 0.00373 -0.0864 0.4453 1.0000
3.750 0.8444 0.00962 0.00388 -0.0843 0.4239 1.0000
4.000 0.8614 0.00989 0.00403 -0.0822 0.4058 1.0000
4.250 0.8793 0.01014 0.00419 -0.0803 0.3912 1.0000
4.500 0.8979 0.01037 0.00437 -0.0785 0.3797 1.0000
4.750 0.9160 0.01064 0.00456 -0.0767 0.3700 1.0000
5.000 0.9354 0.01087 0.00474 -0.0750 0.3612 1.0000
5.250 0.9543 0.01114 0.00495 -0.0734 0.3530 1.0000
5.500 0.9748 0.01136 0.00513 -0.0720 0.3447 1.0000
5.750 0.9944 0.01165 0.00536 -0.0705 0.3368 1.0000
6.000 1.0167 0.01184 0.00556 -0.0695 0.3305 1.0000
6.250 1.0377 0.01211 0.00579 -0.0683 0.3252 1.0000
6.500 1.0588 0.01239 0.00605 -0.0671 0.3202 1.0000
6.750 1.0820 0.01257 0.00626 -0.0663 0.3159 1.0000
7.000 1.1040 0.01281 0.00650 -0.0653 0.3114 1.0000
7.250 1.1245 0.01312 0.00678 -0.0641 0.3067 1.0000
7.500 1.1454 0.01338 0.00705 -0.0629 0.3023 1.0000
7.750 1.1672 0.01357 0.00729 -0.0619 0.2978 1.0000
8.000 1.1876 0.01384 0.00756 -0.0607 0.2931 1.0000
8.250 1.2064 0.01421 0.00790 -0.0593 0.2883 1.0000
8.500 1.2284 0.01442 0.00817 -0.0584 0.2839 1.0000
8.750 1.2496 0.01467 0.00846 -0.0574 0.2785 1.0000
9.000 1.2683 0.01505 0.00881 -0.0560 0.2729 1.0000
9.250 1.2893 0.01533 0.00914 -0.0551 0.2677 1.0000
9.500 1.3099 0.01563 0.00948 -0.0541 0.2614 1.0000
9.750 1.3272 0.01609 0.00991 -0.0527 0.2548 1.0000
10.000 1.3485 0.01637 0.01025 -0.0518 0.2470 1.0000
10.250 1.3656 0.01685 0.01071 -0.0505 0.2375 1.0000
10.500 1.3827 0.01736 0.01120 -0.0492 0.2254 1.0000
10.750 1.3985 0.01796 0.01177 -0.0478 0.2111 1.0000
11.000 1.4109 0.01877 0.01250 -0.0460 0.1944 1.0000
11.250 1.4215 0.01972 0.01338 -0.0442 0.1769 1.0000
11.500 1.4305 0.02082 0.01440 -0.0422 0.1616 1.0000
11.750 1.4390 0.02198 0.01551 -0.0403 0.1491 1.0000
12.000 1.4466 0.02325 0.01672 -0.0384 0.1386 1.0000
12.250 1.4567 0.02438 0.01785 -0.0369 0.1302 1.0000
12.500 1.4652 0.02566 0.01913 -0.0353 0.1234 1.0000
12.750 1.4742 0.02693 0.02041 -0.0339 0.1174 1.0000
13.000 1.4811 0.02840 0.02189 -0.0324 0.1125 1.0000
13.250 1.4916 0.02963 0.02317 -0.0313 0.1087 1.0000
13.500 1.4988 0.03114 0.02471 -0.0301 0.1050 1.0000
13.750 1.5020 0.03302 0.02660 -0.0287 0.1014 1.0000
14.000 1.5126 0.03433 0.02800 -0.0279 0.0990 1.0000
14.250 1.5202 0.03593 0.02965 -0.0269 0.0961 1.0000
14.500 1.5246 0.03787 0.03163 -0.0260 0.0931 1.0000
14.750 1.5247 0.04023 0.03402 -0.0250 0.0902 1.0000
15.000 1.5342 0.04180 0.03568 -0.0245 0.0883 1.0000
15.250 1.5406 0.04369 0.03766 -0.0239 0.0862 1.0000
15.500 1.5443 0.04591 0.03993 -0.0234 0.0841 1.0000
15.750 1.5449 0.04849 0.04256 -0.0229 0.0820 1.0000
16.000 1.5425 0.05144 0.04556 -0.0225 0.0798 1.0000
16.250 1.5502 0.05339 0.04762 -0.0224 0.0778 1.0000
16.500 1.5536 0.05584 0.05015 -0.0223 0.0754 1.0000
16.750 1.5530 0.05881 0.05318 -0.0223 0.0730 1.0000
17.000 1.5470 0.06245 0.05686 -0.0224 0.0708 1.0000
17.250 1.5512 0.06494 0.05946 -0.0225 0.0687 1.0000
17.500 1.5514 0.06796 0.06256 -0.0228 0.0661 1.0000
17.750 1.5464 0.07170 0.06636 -0.0233 0.0635 1.0000
18.000 1.5419 0.07539 0.07013 -0.0238 0.0610 1.0000
18.250 1.5385 0.07901 0.07384 -0.0245 0.0575 1.0000
18.500 1.5281 0.08363 0.07850 -0.0254 0.0541 1.0000
18.750 1.5199 0.08803 0.08297 -0.0264 0.0493 1.0000
19.000 1.5063 0.09324 0.08823 -0.0277 0.0443 1.0000
19.250 1.4892 0.09903 0.09406 -0.0294 0.0390 1.0000
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Polar data table (+)
Polar graphs
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