NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 100,000 Max Cl/Cd: 31.7 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20610-il-100000.txt Download as CSV file: xf-sc20610-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0610 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5663 0.10276 0.09722 -0.0236 1.0000 0.1483
-10.000 -0.5554 0.09992 0.09438 -0.0226 1.0000 0.1531
-9.750 -0.6216 0.09347 0.08817 -0.0331 1.0000 0.1602
-9.500 -0.5725 0.09138 0.08598 -0.0262 1.0000 0.1642
-9.250 -0.5670 0.08841 0.08304 -0.0255 1.0000 0.1696
-9.000 -0.6793 0.08095 0.07569 -0.0393 1.0000 0.1760
-8.750 -0.5924 0.08038 0.07519 -0.0269 1.0000 0.1814
-8.500 -0.7087 0.05047 0.04372 -0.0505 1.0000 0.0881
-8.250 -0.6936 0.04619 0.03919 -0.0504 1.0000 0.0835
-8.000 -0.6777 0.04158 0.03418 -0.0511 1.0000 0.0811
-7.750 -0.6573 0.03738 0.02947 -0.0519 1.0000 0.0798
-7.500 -0.6341 0.03437 0.02600 -0.0525 1.0000 0.0814
-7.250 -0.6086 0.03194 0.02306 -0.0530 1.0000 0.0845
-7.000 -0.5816 0.02981 0.02040 -0.0533 1.0000 0.0867
-6.750 -0.5583 0.02734 0.01794 -0.0532 1.0000 0.0905
-6.500 -0.5330 0.02607 0.01654 -0.0530 1.0000 0.0969
-6.250 -0.5073 0.02441 0.01467 -0.0526 1.0000 0.1024
-6.000 -0.4824 0.02326 0.01356 -0.0523 1.0000 0.1106
-5.750 -0.4572 0.02197 0.01226 -0.0519 1.0000 0.1186
-5.500 -0.4309 0.02115 0.01134 -0.0517 1.0000 0.1298
-5.250 -0.4056 0.02003 0.01044 -0.0513 1.0000 0.1424
-5.000 -0.3787 0.01913 0.00965 -0.0514 1.0000 0.1605
-4.750 -0.3499 0.01809 0.00892 -0.0520 1.0000 0.1897
-4.500 -0.3085 0.01535 0.00855 -0.0563 1.0000 0.5117
-4.250 -0.2978 0.01657 0.00999 -0.0504 1.0000 0.6446
-4.000 -0.2865 0.01766 0.01104 -0.0451 1.0000 0.6786
-3.750 -0.2717 0.01855 0.01184 -0.0410 1.0000 0.7055
-3.500 -0.2614 0.01931 0.01255 -0.0358 1.0000 0.7234
-3.250 -0.2502 0.01992 0.01312 -0.0310 1.0000 0.7408
-3.000 -0.2387 0.02038 0.01356 -0.0265 1.0000 0.7577
-2.750 -0.2287 0.02073 0.01389 -0.0216 1.0000 0.7748
-2.500 -0.2196 0.02096 0.01410 -0.0165 1.0000 0.7927
-2.250 -0.2102 0.02105 0.01417 -0.0118 1.0000 0.8122
-2.000 -0.1979 0.02106 0.01415 -0.0079 1.0000 0.8334
-1.750 -0.1910 0.02079 0.01387 -0.0028 1.0000 0.8516
-1.500 -0.1810 0.02044 0.01350 0.0013 1.0000 0.8697
-1.250 -0.1658 0.02007 0.01311 0.0038 1.0000 0.8849
-1.000 -0.1449 0.01976 0.01277 0.0048 1.0000 0.8958
-0.750 -0.1207 0.01955 0.01252 0.0048 1.0000 0.9043
-0.500 -0.0982 0.01926 0.01222 0.0052 1.0000 0.9115
-0.250 -0.0717 0.01914 0.01209 0.0045 1.0000 0.9181
0.000 -0.0475 0.01896 0.01191 0.0044 1.0000 0.9242
0.250 -0.0217 0.01888 0.01185 0.0039 1.0000 0.9299
0.500 0.0078 0.01895 0.01194 0.0024 1.0000 0.9340
0.750 0.0331 0.01890 0.01193 0.0019 1.0000 0.9385
1.000 0.0610 0.01899 0.01207 0.0007 1.0000 0.9427
1.250 0.0902 0.01918 0.01233 -0.0008 1.0000 0.9468
1.500 0.1164 0.01931 0.01254 -0.0017 1.0000 0.9511
1.750 0.1433 0.01954 0.01287 -0.0029 1.0000 0.9558
2.000 0.2138 0.01981 0.01329 -0.0116 0.9761 0.9576
2.250 0.2948 0.01933 0.01301 -0.0207 0.9442 0.9587
2.500 0.3603 0.01825 0.01214 -0.0260 0.9141 0.9601
2.750 0.4143 0.01685 0.01097 -0.0285 0.8815 0.9619
3.000 0.4567 0.01539 0.00971 -0.0283 0.8293 0.9643
3.250 0.5028 0.01586 0.00794 -0.0269 0.3427 0.9644
3.500 0.5186 0.01778 0.00875 -0.0253 0.2007 0.9687
3.750 0.5434 0.01881 0.00952 -0.0251 0.1659 0.9731
4.000 0.5723 0.01985 0.01036 -0.0257 0.1457 0.9772
4.250 0.6034 0.02097 0.01138 -0.0266 0.1304 0.9818
4.500 0.6373 0.02221 0.01263 -0.0280 0.1179 0.9866
4.750 0.6722 0.02379 0.01421 -0.0296 0.1084 0.9922
5.000 0.7026 0.02506 0.01549 -0.0304 0.0996 1.0000
5.250 0.7336 0.02702 0.01769 -0.0312 0.0938 1.0000
5.500 0.7633 0.02851 0.01934 -0.0319 0.0875 1.0000
5.750 0.7933 0.03154 0.02242 -0.0331 0.0835 1.0000
6.000 0.8205 0.03386 0.02527 -0.0331 0.0819 1.0000
6.250 0.8457 0.03648 0.02846 -0.0328 0.0798 1.0000
6.500 0.8686 0.03955 0.03205 -0.0326 0.0779 1.0000
6.750 0.8884 0.04370 0.03671 -0.0321 0.0792 1.0000
7.000 0.9064 0.04834 0.04172 -0.0319 0.0813 1.0000
7.250 0.8627 0.07130 0.06714 -0.0319 0.1793 1.0000
7.500 0.8915 0.07537 0.07111 -0.0319 0.1746 1.0000
7.750 0.8600 0.08053 0.07660 -0.0344 0.1641 1.0000
8.000 0.7796 0.07719 0.07335 -0.0191 0.1729 1.0000
8.250 0.6943 0.08478 0.08112 -0.0238 0.1713 1.0000
8.500 0.6552 0.09282 0.08913 -0.0308 0.1646 1.0000
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Polar data table (+)
Polar graphs
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