NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.34 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20503-il-1000000.txt Download as CSV file: xf-sc20503-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0503 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.000 -0.4730 0.02913 0.02712 -0.0297 1.0000 0.0048
-5.750 -0.4535 0.02418 0.02198 -0.0318 1.0000 0.0050
-5.500 -0.4317 0.02019 0.01781 -0.0335 1.0000 0.0052
-5.250 -0.4081 0.01685 0.01427 -0.0348 1.0000 0.0055
-5.000 -0.3823 0.01387 0.01105 -0.0360 1.0000 0.0059
-4.750 -0.3548 0.01126 0.00819 -0.0370 1.0000 0.0065
-4.500 -0.3261 0.00906 0.00572 -0.0378 1.0000 0.0072
-4.250 -0.2969 0.00735 0.00372 -0.0383 1.0000 0.0082
-4.000 -0.2689 0.00659 0.00278 -0.0380 1.0000 0.0099
-2.500 -0.0843 0.00657 0.00110 -0.0429 1.0000 0.0096
-2.250 -0.0566 0.00631 0.00086 -0.0429 1.0000 0.0288
-2.000 -0.0218 0.00464 0.00066 -0.0459 1.0000 0.4844
-1.750 0.0073 0.00413 0.00065 -0.0465 1.0000 0.6508
-1.500 0.0346 0.00394 0.00069 -0.0464 1.0000 0.7288
-1.250 0.0613 0.00381 0.00075 -0.0461 1.0000 0.7884
-1.000 0.0880 0.00376 0.00078 -0.0458 1.0000 0.8156
-0.750 0.1147 0.00373 0.00082 -0.0456 1.0000 0.8340
-0.500 0.1415 0.00371 0.00087 -0.0453 1.0000 0.8491
-0.250 0.1682 0.00369 0.00093 -0.0451 1.0000 0.8637
0.000 0.2189 0.00407 0.00081 -0.0498 0.7891 0.8735
0.250 0.2391 0.00571 0.00099 -0.0487 0.3684 0.8869
0.500 0.2629 0.00704 0.00121 -0.0485 0.0213 0.9012
1.000 0.3120 0.00740 0.00172 -0.0466 0.0057 0.9421
1.250 0.3351 0.00872 0.00334 -0.0451 0.0041 1.0000
1.500 0.3628 0.00987 0.00457 -0.0448 0.0043 1.0000
1.750 0.3918 0.01182 0.00674 -0.0438 0.0072 1.0000
2.000 0.4045 0.00567 0.00128 -0.0395 0.0102 1.0000
2.250 0.4306 0.00689 0.00278 -0.0387 0.0101 1.0000
2.500 0.4592 0.00709 0.00317 -0.0381 0.0089 1.0000
2.750 0.4857 0.00820 0.00450 -0.0372 0.0075 1.0000
3.000 0.5107 0.00997 0.00654 -0.0362 0.0066 1.0000
3.250 0.5347 0.01219 0.00902 -0.0352 0.0060 1.0000
3.500 0.5577 0.01477 0.01185 -0.0344 0.0056 1.0000
3.750 0.5796 0.01776 0.01505 -0.0338 0.0052 1.0000
4.000 0.6002 0.02112 0.01861 -0.0334 0.0049 1.0000
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Polar data table (+)
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