NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 50,000 Max Cl/Cd: 19.39 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20503-il-50000.txt Download as CSV file: xf-sc20503-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6764 0.10599 0.09937 0.0173 1.0000 0.1789
-8.000 -0.6692 0.10172 0.09514 0.0173 1.0000 0.1916
-7.750 -0.6652 0.09795 0.09142 0.0152 1.0000 0.2050
-7.500 -0.6532 0.09344 0.08694 0.0192 1.0000 0.2266
-7.250 -0.6542 0.09037 0.08394 0.0135 1.0000 0.2448
-7.000 -0.6416 0.08623 0.07984 0.0201 1.0000 0.2774
-6.750 -0.6395 0.08326 0.07694 0.0188 1.0000 0.3104
-6.250 -0.6181 0.07638 0.07014 0.0301 1.0000 0.3983
-6.000 -0.6079 0.07329 0.06709 0.0359 1.0000 0.4524
-5.750 -0.5938 0.07013 0.06396 0.0431 1.0000 0.5194
-4.750 -0.4105 0.03866 0.02974 -0.0374 1.0000 0.1515
-4.500 -0.3718 0.03416 0.02449 -0.0390 1.0000 0.1184
-4.250 -0.3335 0.03119 0.02046 -0.0396 1.0000 0.0999
-4.000 -0.3030 0.02781 0.01646 -0.0394 1.0000 0.0930
-3.750 -0.2716 0.02537 0.01344 -0.0387 1.0000 0.0895
-3.500 -0.2439 0.02326 0.01114 -0.0378 1.0000 0.0971
-3.250 -0.2187 0.02141 0.00920 -0.0362 1.0000 0.1112
-3.000 -0.1927 0.01961 0.00732 -0.0345 1.0000 0.1237
-2.750 -0.1630 0.01746 0.00543 -0.0345 1.0000 0.1748
-2.500 -0.1688 0.01347 0.00467 -0.0227 1.0000 1.0000
-2.250 -0.1399 0.01338 0.00368 -0.0226 1.0000 1.0000
-2.000 -0.1118 0.01330 0.00311 -0.0229 1.0000 1.0000
-1.750 -0.0839 0.01324 0.00269 -0.0232 1.0000 1.0000
-1.500 -0.0561 0.01320 0.00238 -0.0235 1.0000 1.0000
-1.250 -0.0285 0.01318 0.00210 -0.0237 1.0000 1.0000
-1.000 -0.0010 0.01317 0.00193 -0.0239 1.0000 1.0000
-0.750 0.0263 0.01318 0.00183 -0.0240 1.0000 1.0000
-0.500 0.0535 0.01320 0.00180 -0.0241 1.0000 1.0000
-0.250 0.0806 0.01323 0.00185 -0.0242 1.0000 1.0000
0.000 0.1076 0.01327 0.00196 -0.0242 1.0000 1.0000
0.250 0.1344 0.01333 0.00214 -0.0242 1.0000 1.0000
0.500 0.1612 0.01340 0.00239 -0.0241 1.0000 1.0000
0.750 0.1879 0.01349 0.00278 -0.0240 1.0000 1.0000
1.000 0.2146 0.01359 0.00319 -0.0239 1.0000 1.0000
1.250 0.2413 0.01371 0.00373 -0.0237 1.0000 1.0000
1.500 0.2683 0.01384 0.00454 -0.0233 1.0000 1.0000
1.750 0.3381 0.01976 0.00755 -0.0283 0.1213 1.0000
2.000 0.3697 0.02176 0.00968 -0.0276 0.1086 1.0000
2.250 0.4013 0.02391 0.01197 -0.0271 0.0951 1.0000
2.500 0.4317 0.02628 0.01452 -0.0266 0.0882 1.0000
2.750 0.4640 0.02879 0.01765 -0.0257 0.0928 1.0000
3.000 0.4954 0.03182 0.02147 -0.0249 0.1013 1.0000
3.250 0.5294 0.03502 0.02556 -0.0242 0.1199 1.0000
3.500 0.5648 0.03899 0.03026 -0.0239 0.1537 1.0000
4.000 0.6439 0.05641 0.05072 -0.1061 0.7869 1.0000
4.250 0.6157 0.05827 0.05244 -0.1046 0.8304 1.0000
4.500 0.6439 0.06308 0.05727 -0.1068 0.7951 1.0000
5.250 0.7782 0.07714 0.07172 -0.0683 0.3886 1.0000
6.000 0.7942 0.08804 0.08243 -0.0568 0.2557 1.0000
6.250 0.7996 0.09214 0.08650 -0.0563 0.2293 1.0000
6.500 0.8107 0.09704 0.09133 -0.0520 0.2047 1.0000
6.750 0.8136 0.10118 0.09547 -0.0550 0.1910 1.0000
7.000 0.8192 0.10579 0.10006 -0.0558 0.1780 1.0000
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Polar data table (+)
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