NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 500,000 Max Cl/Cd: 50.18 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20503-il-500000.txt Download as CSV file: xf-sc20503-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6500 0.09687 0.09466 0.0178 1.0000 0.0084
-8.250 -0.6462 0.09302 0.09082 0.0155 1.0000 0.0086
-8.000 -0.6424 0.08912 0.08695 0.0129 1.0000 0.0088
-7.750 -0.6343 0.08469 0.08253 0.0083 1.0000 0.0090
-7.500 -0.6220 0.07968 0.07748 0.0018 1.0000 0.0092
-7.250 -0.6060 0.07425 0.07203 -0.0055 1.0000 0.0095
-7.000 -0.5867 0.06894 0.06665 -0.0122 1.0000 0.0098
-6.750 -0.5642 0.06413 0.06176 -0.0176 1.0000 0.0102
-6.500 -0.5413 0.05978 0.05730 -0.0215 1.0000 0.0105
-6.250 -0.5187 0.05534 0.05272 -0.0247 1.0000 0.0106
-6.000 -0.4956 0.05092 0.04814 -0.0274 1.0000 0.0107
-5.750 -0.4716 0.04661 0.04364 -0.0296 1.0000 0.0107
-5.500 -0.4465 0.04243 0.03924 -0.0315 1.0000 0.0108
-5.250 -0.4204 0.03842 0.03498 -0.0331 1.0000 0.0108
-5.000 -0.3926 0.03151 0.02767 -0.0360 1.0000 0.0113
-4.750 -0.3642 0.02606 0.02185 -0.0386 1.0000 0.0125
-4.500 -0.3358 0.02325 0.01881 -0.0397 1.0000 0.0137
-4.250 -0.3059 0.02077 0.01604 -0.0405 1.0000 0.0152
-4.000 -0.2753 0.01853 0.01347 -0.0409 1.0000 0.0169
-3.750 -0.2445 0.01637 0.01090 -0.0411 1.0000 0.0178
-3.250 -0.1825 0.01157 0.00549 -0.0403 1.0000 0.0086
-3.000 -0.1524 0.00994 0.00371 -0.0405 1.0000 0.0083
-2.750 -0.1223 0.00893 0.00259 -0.0409 1.0000 0.0099
-2.500 -0.0921 0.00811 0.00169 -0.0414 1.0000 0.0175
-2.250 -0.0547 0.00559 0.00101 -0.0452 1.0000 0.5783
-2.000 -0.0278 0.00517 0.00105 -0.0450 1.0000 0.7291
-1.750 -0.0032 0.00500 0.00111 -0.0440 1.0000 0.8042
-1.500 0.0195 0.00491 0.00114 -0.0425 1.0000 0.8561
-1.250 0.0430 0.00483 0.00113 -0.0413 1.0000 0.8818
-1.000 0.0666 0.00476 0.00110 -0.0402 1.0000 0.9021
-0.750 0.0882 0.00465 0.00106 -0.0387 1.0000 0.9248
-0.500 0.1062 0.00447 0.00098 -0.0362 1.0000 0.9671
-0.250 0.1324 0.00447 0.00100 -0.0360 1.0000 1.0000
0.000 0.1617 0.00450 0.00107 -0.0366 1.0000 1.0000
0.250 0.1907 0.00454 0.00119 -0.0369 1.0000 1.0000
0.500 0.2519 0.00502 0.00102 -0.0436 0.7234 1.0000
0.750 0.2699 0.00818 0.00162 -0.0427 0.0280 1.0000
1.000 0.2982 0.00891 0.00239 -0.0428 0.0113 1.0000
1.250 0.3261 0.00978 0.00334 -0.0426 0.0088 1.0000
1.500 0.3537 0.01104 0.00471 -0.0421 0.0079 1.0000
1.750 0.3815 0.01293 0.00677 -0.0414 0.0084 1.0000
2.000 0.4114 0.01513 0.00923 -0.0404 0.0139 1.0000
2.250 0.4408 0.01773 0.01219 -0.0394 0.0164 1.0000
2.500 0.4693 0.01987 0.01473 -0.0387 0.0154 1.0000
2.750 0.4968 0.02210 0.01726 -0.0381 0.0140 1.0000
3.000 0.5231 0.02453 0.01997 -0.0377 0.0127 1.0000
3.250 0.5477 0.02734 0.02301 -0.0374 0.0117 1.0000
3.500 0.5688 0.03252 0.02855 -0.0372 0.0107 1.0000
3.750 0.5893 0.03890 0.03533 -0.0368 0.0102 1.0000
4.000 0.6126 0.04267 0.03935 -0.0365 0.0102 1.0000
4.250 0.6353 0.04659 0.04351 -0.0365 0.0102 1.0000
4.500 0.6576 0.05066 0.04779 -0.0367 0.0101 1.0000
4.750 0.6794 0.05481 0.05213 -0.0372 0.0100 1.0000
5.000 0.7014 0.05891 0.05640 -0.0381 0.0099 1.0000
5.250 0.7248 0.06270 0.06034 -0.0394 0.0095 1.0000
5.500 0.7479 0.06702 0.06479 -0.0416 0.0090 1.0000
5.750 0.7672 0.07193 0.06982 -0.0445 0.0086 1.0000
6.000 0.7833 0.07707 0.07509 -0.0480 0.0083 1.0000
6.250 0.7967 0.08230 0.08038 -0.0521 0.0080 1.0000
6.500 0.8077 0.08755 0.08568 -0.0565 0.0078 1.0000
6.750 0.8162 0.09273 0.09088 -0.0612 0.0077 1.0000
7.000 0.8220 0.09777 0.09593 -0.0660 0.0076 1.0000
7.250 0.8224 0.10228 0.10043 -0.0698 0.0075 1.0000
7.500 0.8229 0.10663 0.10476 -0.0726 0.0074 1.0000
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Polar data table (+)
Polar graphs
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