CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 50,000 Max Cl/Cd: 12.29 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarym15-il-50000.txt Download as CSV file: xf-clarym15-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3134 0.11547 0.10839 -0.0283 1.0000 0.2926
-9.000 -0.2942 0.11166 0.10459 -0.0267 1.0000 0.2991
-8.750 -0.3224 0.11190 0.10499 -0.0244 1.0000 0.3080
-8.500 -0.3194 0.10864 0.10180 -0.0227 1.0000 0.3123
-8.250 -0.3126 0.10619 0.09939 -0.0204 1.0000 0.3206
-8.000 -0.3678 0.10810 0.10154 -0.0164 1.0000 0.3274
-7.750 -0.3296 0.10277 0.09617 -0.0152 1.0000 0.3359
-7.500 -0.3691 0.10340 0.09698 -0.0112 1.0000 0.3449
-7.250 -0.3530 0.09973 0.09332 -0.0094 1.0000 0.3523
-7.000 -0.3851 0.09977 0.09352 -0.0052 1.0000 0.3628
-6.750 -0.3802 0.09677 0.09057 -0.0031 1.0000 0.3696
-6.500 -0.4064 0.09633 0.09024 0.0012 1.0000 0.3806
-6.250 -0.4105 0.09380 0.08779 0.0038 1.0000 0.3874
-6.000 -0.5623 0.06799 0.06125 -0.0253 1.0000 0.1845
-5.750 -0.5560 0.06435 0.05754 -0.0249 1.0000 0.1821
-5.500 -0.5499 0.05990 0.05285 -0.0255 1.0000 0.1787
-5.250 -0.5415 0.05386 0.04618 -0.0276 1.0000 0.1734
-5.000 -0.5266 0.04894 0.04046 -0.0291 1.0000 0.1706
-4.750 -0.5098 0.04683 0.03823 -0.0286 1.0000 0.1729
-4.500 -0.4921 0.04506 0.03627 -0.0283 1.0000 0.1771
-4.250 -0.4723 0.04290 0.03368 -0.0284 1.0000 0.1819
-4.000 -0.4507 0.04073 0.03097 -0.0286 1.0000 0.1867
-3.750 -0.4317 0.03976 0.03006 -0.0281 1.0000 0.1940
-3.500 -0.4098 0.03842 0.02834 -0.0280 1.0000 0.2043
-3.250 -0.3895 0.03764 0.02752 -0.0276 1.0000 0.2162
-3.000 -0.3689 0.03691 0.02676 -0.0273 1.0000 0.2306
-2.750 -0.3481 0.03634 0.02614 -0.0270 1.0000 0.2489
-2.500 -0.3269 0.03589 0.02559 -0.0268 1.0000 0.2712
-2.250 -0.3064 0.03548 0.02531 -0.0265 1.0000 0.2956
-2.000 -0.2851 0.03517 0.02500 -0.0263 1.0000 0.3265
-1.750 -0.2330 0.03513 0.02528 -0.0312 0.9886 0.3878
-1.500 -0.1843 0.03504 0.02565 -0.0352 0.9769 0.4794
-1.250 -0.1418 0.03482 0.02621 -0.0374 0.9644 0.6047
-1.000 -0.1101 0.03447 0.02715 -0.0345 0.9514 0.8699
-0.750 -0.0381 0.03524 0.02723 -0.0448 0.9305 1.0000
-0.500 0.0052 0.03606 0.02762 -0.0487 0.9134 1.0000
-0.250 0.0445 0.03684 0.02807 -0.0516 0.8976 1.0000
0.000 0.0826 0.03760 0.02857 -0.0542 0.8824 1.0000
0.250 0.1217 0.03834 0.02907 -0.0567 0.8675 1.0000
0.500 0.1655 0.03904 0.02955 -0.0598 0.8532 1.0000
0.750 0.1972 0.03964 0.02999 -0.0610 0.8378 1.0000
1.000 0.2267 0.04024 0.03045 -0.0617 0.8217 1.0000
1.250 0.2564 0.04085 0.03093 -0.0624 0.8056 1.0000
1.500 0.2863 0.04144 0.03141 -0.0630 0.7894 1.0000
1.750 0.3166 0.04201 0.03188 -0.0635 0.7731 1.0000
2.000 0.3467 0.04256 0.03235 -0.0640 0.7570 1.0000
2.250 0.3766 0.04310 0.03281 -0.0643 0.7412 1.0000
2.500 0.4082 0.04356 0.03320 -0.0648 0.7259 1.0000
2.750 0.4597 0.04325 0.03282 -0.0672 0.7148 1.0000
3.000 0.4792 0.04405 0.03357 -0.0662 0.6987 1.0000
3.250 0.4966 0.04503 0.03451 -0.0651 0.6830 1.0000
3.500 0.5133 0.04611 0.03556 -0.0640 0.6681 1.0000
3.750 0.5322 0.04719 0.03660 -0.0632 0.6547 1.0000
4.250 0.5768 0.04914 0.03850 -0.0623 0.6320 1.0000
4.500 0.5829 0.05121 0.04055 -0.0609 0.6198 1.0000
4.750 0.6254 0.05088 0.04022 -0.0616 0.6123 1.0000
5.000 0.6082 0.05481 0.04413 -0.0594 0.5998 1.0000
5.250 0.6591 0.05391 0.04324 -0.0604 0.5940 1.0000
5.500 0.6273 0.05910 0.04842 -0.0579 0.5818 1.0000
5.750 0.6662 0.05917 0.04851 -0.0583 0.5754 1.0000
6.000 0.6342 0.06462 0.05396 -0.0564 0.5661 1.0000
6.250 0.6831 0.06398 0.05335 -0.0570 0.5597 1.0000
6.500 0.6431 0.07016 0.05953 -0.0553 0.5519 1.0000
6.750 0.6635 0.07181 0.06121 -0.0552 0.5450 1.0000
7.000 0.6635 0.07504 0.06446 -0.0547 0.5384 1.0000
7.250 0.6537 0.07901 0.06845 -0.0542 0.5327 1.0000
7.500 0.6965 0.07907 0.06857 -0.0543 0.5241 1.0000
7.750 0.6675 0.08456 0.07409 -0.0537 0.5197 1.0000
8.000 0.6649 0.08813 0.07770 -0.0536 0.5147 1.0000
8.250 0.6895 0.08964 0.07925 -0.0534 0.5051 1.0000
8.500 0.6749 0.09422 0.08388 -0.0534 0.5019 1.0000
8.750 0.7102 0.09488 0.08460 -0.0529 0.4892 1.0000
9.000 0.6902 0.09995 0.08971 -0.0531 0.4864 1.0000
9.250 0.6816 0.10437 0.09419 -0.0535 0.4845 1.0000
9.500 0.6763 0.10863 0.09852 -0.0540 0.4834 1.0000
9.750 0.6777 0.11338 0.10333 -0.0553 0.4876 1.0000
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Polar data table (+)
Polar graphs
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