CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 500,000 Max Cl/Cd: 84.39 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarym15-il-500000-n5.txt Download as CSV file: xf-clarym15-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7827 0.09164 0.08832 -0.0600 1.0000 0.0259
-16.250 -0.8386 0.07833 0.07477 -0.0686 1.0000 0.0259
-16.000 -0.8735 0.06885 0.06511 -0.0750 1.0000 0.0260
-15.750 -0.8989 0.06092 0.05701 -0.0807 1.0000 0.0260
-15.500 -0.9171 0.05414 0.05005 -0.0859 1.0000 0.0261
-15.250 -0.9296 0.04844 0.04417 -0.0905 1.0000 0.0262
-15.000 -0.9380 0.04379 0.03936 -0.0941 1.0000 0.0262
-14.750 -0.9437 0.04009 0.03550 -0.0965 1.0000 0.0263
-14.500 -0.9506 0.03697 0.03227 -0.0974 1.0000 0.0264
-14.250 -0.9576 0.03459 0.02980 -0.0968 1.0000 0.0266
-14.000 -0.9672 0.03284 0.02798 -0.0944 1.0000 0.0267
-13.750 -0.9774 0.03152 0.02658 -0.0909 0.9994 0.0268
-13.500 -0.9612 0.02995 0.02492 -0.0919 0.9952 0.0270
-13.250 -0.9429 0.02866 0.02356 -0.0926 0.9909 0.0273
-13.000 -0.9219 0.02751 0.02233 -0.0932 0.9863 0.0275
-12.750 -0.8975 0.02643 0.02117 -0.0943 0.9832 0.0279
-12.500 -0.8758 0.02545 0.02010 -0.0946 0.9785 0.0282
-12.250 -0.8532 0.02448 0.01904 -0.0949 0.9735 0.0284
-12.000 -0.8281 0.02353 0.01799 -0.0955 0.9700 0.0287
-11.750 -0.8076 0.02271 0.01707 -0.0950 0.9633 0.0290
-11.500 -0.7838 0.02189 0.01616 -0.0951 0.9581 0.0293
-11.250 -0.7611 0.02115 0.01533 -0.0948 0.9524 0.0296
-11.000 -0.7390 0.02047 0.01455 -0.0943 0.9455 0.0299
-10.750 -0.7146 0.01983 0.01381 -0.0941 0.9403 0.0302
-10.500 -0.6928 0.01930 0.01319 -0.0933 0.9324 0.0304
-10.250 -0.6705 0.01858 0.01240 -0.0927 0.9257 0.0308
-10.000 -0.6489 0.01791 0.01169 -0.0919 0.9181 0.0312
-9.750 -0.6260 0.01733 0.01106 -0.0913 0.9107 0.0315
-9.500 -0.6026 0.01682 0.01049 -0.0907 0.9034 0.0319
-9.250 -0.5788 0.01635 0.00996 -0.0901 0.8953 0.0322
-9.000 -0.5544 0.01591 0.00945 -0.0895 0.8878 0.0326
-8.750 -0.5300 0.01548 0.00897 -0.0890 0.8794 0.0331
-8.500 -0.5052 0.01509 0.00849 -0.0885 0.8718 0.0335
-8.250 -0.4802 0.01471 0.00805 -0.0880 0.8633 0.0340
-8.000 -0.4548 0.01436 0.00761 -0.0876 0.8558 0.0344
-7.750 -0.4293 0.01403 0.00722 -0.0872 0.8476 0.0349
-7.500 -0.4037 0.01370 0.00682 -0.0868 0.8402 0.0354
-7.250 -0.3784 0.01332 0.00641 -0.0864 0.8326 0.0363
-7.000 -0.3525 0.01302 0.00607 -0.0860 0.8251 0.0371
-6.750 -0.3262 0.01274 0.00575 -0.0857 0.8181 0.0380
-6.500 -0.2998 0.01249 0.00544 -0.0854 0.8108 0.0389
-6.250 -0.2732 0.01226 0.00515 -0.0851 0.8041 0.0399
-6.000 -0.2466 0.01201 0.00487 -0.0848 0.7967 0.0411
-5.750 -0.2201 0.01178 0.00460 -0.0845 0.7893 0.0429
-5.500 -0.1934 0.01157 0.00437 -0.0842 0.7813 0.0452
-5.250 -0.1669 0.01137 0.00414 -0.0839 0.7723 0.0483
-5.000 -0.1401 0.01118 0.00393 -0.0836 0.7632 0.0532
-4.750 -0.1135 0.01101 0.00375 -0.0833 0.7543 0.0604
-4.500 -0.0865 0.01084 0.00360 -0.0831 0.7461 0.0683
-4.250 -0.0596 0.01070 0.00344 -0.0828 0.7378 0.0757
-4.000 -0.0325 0.01056 0.00330 -0.0826 0.7288 0.0817
-3.750 -0.0056 0.01046 0.00316 -0.0823 0.7194 0.0877
-3.500 0.0216 0.01033 0.00303 -0.0821 0.7112 0.0938
-3.250 0.0487 0.01024 0.00291 -0.0819 0.7028 0.1004
-3.000 0.0756 0.01012 0.00279 -0.0816 0.6930 0.1087
-2.750 0.1022 0.01001 0.00268 -0.0813 0.6823 0.1200
-2.500 0.1286 0.00986 0.00258 -0.0810 0.6712 0.1410
-2.250 0.1547 0.00969 0.00250 -0.0807 0.6601 0.1738
-2.000 0.1809 0.00957 0.00244 -0.0803 0.6499 0.2032
-1.750 0.2079 0.00948 0.00240 -0.0801 0.6405 0.2273
-1.500 0.2345 0.00941 0.00236 -0.0798 0.6311 0.2496
-1.250 0.2613 0.00934 0.00233 -0.0796 0.6204 0.2703
-1.000 0.2880 0.00930 0.00230 -0.0793 0.6095 0.2901
-0.750 0.3143 0.00928 0.00228 -0.0789 0.5979 0.3092
-0.500 0.3410 0.00925 0.00227 -0.0786 0.5863 0.3299
-0.250 0.3674 0.00921 0.00226 -0.0783 0.5756 0.3553
0.250 0.4179 0.00895 0.00229 -0.0774 0.5526 0.4691
0.500 0.4424 0.00880 0.00233 -0.0767 0.5412 0.5402
0.750 0.4655 0.00861 0.00240 -0.0758 0.5290 0.6332
1.000 0.4883 0.00845 0.00248 -0.0746 0.5157 0.7214
1.250 0.5118 0.00841 0.00258 -0.0736 0.5012 0.7791
1.500 0.5356 0.00845 0.00269 -0.0725 0.4858 0.8252
1.750 0.5596 0.00853 0.00281 -0.0715 0.4698 0.8663
2.000 0.5847 0.00868 0.00294 -0.0707 0.4526 0.8981
2.250 0.6112 0.00888 0.00307 -0.0703 0.4334 0.9221
2.500 0.6399 0.00912 0.00322 -0.0705 0.4129 0.9421
2.750 0.6702 0.00938 0.00337 -0.0711 0.3936 0.9575
3.000 0.7009 0.00964 0.00353 -0.0718 0.3770 0.9696
3.250 0.7340 0.00991 0.00371 -0.0731 0.3628 0.9804
3.500 0.7723 0.01016 0.00389 -0.0754 0.3515 0.9899
3.750 0.8125 0.01042 0.00408 -0.0783 0.3427 0.9968
4.000 0.8444 0.01061 0.00423 -0.0793 0.3363 1.0000
4.250 0.8638 0.01079 0.00437 -0.0777 0.3307 1.0000
4.500 0.8833 0.01098 0.00453 -0.0761 0.3257 1.0000
4.750 0.9040 0.01113 0.00467 -0.0747 0.3210 1.0000
5.000 0.9241 0.01132 0.00483 -0.0732 0.3155 1.0000
5.250 0.9436 0.01157 0.00502 -0.0716 0.3089 1.0000
5.500 0.9656 0.01173 0.00518 -0.0706 0.3025 1.0000
5.750 0.9860 0.01198 0.00538 -0.0692 0.2950 1.0000
6.000 1.0079 0.01219 0.00558 -0.0682 0.2897 1.0000
6.250 1.0306 0.01237 0.00576 -0.0673 0.2853 1.0000
6.500 1.0526 0.01259 0.00597 -0.0663 0.2807 1.0000
6.750 1.0736 0.01285 0.00621 -0.0651 0.2762 1.0000
7.000 1.0957 0.01304 0.00642 -0.0641 0.2728 1.0000
7.250 1.1173 0.01324 0.00664 -0.0631 0.2688 1.0000
7.500 1.1379 0.01349 0.00689 -0.0618 0.2639 1.0000
7.750 1.1575 0.01379 0.00718 -0.0605 0.2588 1.0000
8.000 1.1795 0.01401 0.00743 -0.0596 0.2538 1.0000
8.250 1.2002 0.01430 0.00772 -0.0585 0.2480 1.0000
8.500 1.2198 0.01464 0.00805 -0.0573 0.2423 1.0000
8.750 1.2407 0.01494 0.00837 -0.0563 0.2350 1.0000
9.000 1.2593 0.01534 0.00875 -0.0550 0.2266 1.0000
9.250 1.2784 0.01575 0.00914 -0.0538 0.2164 1.0000
9.500 1.2961 0.01622 0.00960 -0.0525 0.2055 1.0000
9.750 1.3123 0.01680 0.01012 -0.0510 0.1925 1.0000
10.000 1.3264 0.01750 0.01075 -0.0493 0.1777 1.0000
10.250 1.3387 0.01834 0.01151 -0.0475 0.1623 1.0000
10.500 1.3502 0.01924 0.01234 -0.0456 0.1480 1.0000
10.750 1.3618 0.02017 0.01321 -0.0439 0.1357 1.0000
11.000 1.3735 0.02111 0.01412 -0.0422 0.1260 1.0000
11.250 1.3855 0.02207 0.01506 -0.0407 0.1177 1.0000
11.500 1.3986 0.02297 0.01597 -0.0393 0.1117 1.0000
11.750 1.4101 0.02400 0.01699 -0.0379 0.1059 1.0000
12.000 1.4223 0.02501 0.01802 -0.0366 0.1015 1.0000
12.250 1.4343 0.02605 0.01910 -0.0354 0.0972 1.0000
12.500 1.4437 0.02731 0.02036 -0.0341 0.0927 1.0000
12.750 1.4551 0.02845 0.02153 -0.0330 0.0892 1.0000
13.000 1.4652 0.02971 0.02283 -0.0318 0.0859 1.0000
13.250 1.4738 0.03113 0.02427 -0.0307 0.0829 1.0000
13.500 1.4827 0.03254 0.02573 -0.0297 0.0805 1.0000
13.750 1.4925 0.03391 0.02717 -0.0288 0.0785 1.0000
14.000 1.5007 0.03545 0.02876 -0.0279 0.0762 1.0000
14.250 1.5071 0.03719 0.03055 -0.0270 0.0738 1.0000
14.500 1.5119 0.03913 0.03252 -0.0262 0.0714 1.0000
14.750 1.5197 0.04082 0.03429 -0.0255 0.0691 1.0000
15.000 1.5254 0.04278 0.03631 -0.0249 0.0667 1.0000
15.250 1.5287 0.04501 0.03859 -0.0243 0.0643 1.0000
15.500 1.5313 0.04739 0.04102 -0.0239 0.0621 1.0000
15.750 1.5355 0.04963 0.04334 -0.0235 0.0598 1.0000
16.000 1.5371 0.05220 0.04597 -0.0233 0.0571 1.0000
16.250 1.5359 0.05517 0.04900 -0.0231 0.0544 1.0000
16.500 1.5359 0.05806 0.05195 -0.0231 0.0511 1.0000
16.750 1.5312 0.06155 0.05549 -0.0232 0.0475 1.0000
17.000 1.5271 0.06505 0.05905 -0.0234 0.0435 1.0000
17.250 1.5187 0.06917 0.06321 -0.0238 0.0390 1.0000
17.500 1.5066 0.07386 0.06794 -0.0244 0.0333 1.0000
17.750 1.4877 0.07954 0.07365 -0.0254 0.0264 1.0000
18.000 1.4671 0.08562 0.07978 -0.0267 0.0215 1.0000
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