NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 50,000 Max Cl/Cd: 19.38 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20503-il-50000-n5.txt Download as CSV file: xf-sc20503-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6668 0.11682 0.10986 0.0200 1.0000 0.0756
-9.000 -0.6715 0.11447 0.10762 0.0148 1.0000 0.0776
-8.750 -0.6741 0.11158 0.10483 0.0091 1.0000 0.0781
-8.500 -0.6589 0.10521 0.09843 0.0145 1.0000 0.0813
-8.250 -0.6541 0.10137 0.09463 0.0133 1.0000 0.0843
-8.000 -0.6511 0.09761 0.09093 0.0086 1.0000 0.0887
-7.750 -0.6462 0.09295 0.08633 0.0001 1.0000 0.0921
-7.500 -0.6366 0.08850 0.08190 0.0014 1.0000 0.0949
-7.250 -0.6264 0.08407 0.07746 -0.0019 1.0000 0.0985
-7.000 -0.6161 0.07924 0.07260 -0.0081 1.0000 0.1066
-6.500 -0.5643 0.06620 0.05905 -0.0187 1.0000 0.0369
-6.250 -0.5476 0.06133 0.05407 -0.0212 1.0000 0.0338
-6.000 -0.5259 0.05638 0.04887 -0.0246 1.0000 0.0321
-5.750 -0.5018 0.05167 0.04385 -0.0277 1.0000 0.0318
-5.500 -0.4758 0.04731 0.03910 -0.0304 1.0000 0.0331
-5.250 -0.4476 0.04322 0.03454 -0.0327 1.0000 0.0348
-5.000 -0.4178 0.03939 0.03015 -0.0346 1.0000 0.0360
-4.750 -0.3877 0.03575 0.02597 -0.0358 1.0000 0.0359
-4.500 -0.3574 0.03234 0.02202 -0.0366 1.0000 0.0347
-4.250 -0.3270 0.02933 0.01847 -0.0369 1.0000 0.0340
-4.000 -0.2973 0.02674 0.01496 -0.0366 1.0000 0.0335
-3.750 -0.2692 0.02450 0.01232 -0.0357 1.0000 0.0347
-3.500 -0.2429 0.02263 0.01013 -0.0343 1.0000 0.0369
-3.250 -0.2180 0.02091 0.00821 -0.0331 1.0000 0.0424
-3.000 -0.1907 0.01950 0.00664 -0.0330 1.0000 0.0619
-2.750 -0.1607 0.01780 0.00485 -0.0333 1.0000 0.0911
-2.500 -0.1634 0.01409 0.00465 -0.0255 1.0000 0.8300
-2.250 -0.1399 0.01338 0.00362 -0.0226 1.0000 1.0000
-2.000 -0.1118 0.01330 0.00306 -0.0229 1.0000 1.0000
-1.750 -0.0838 0.01324 0.00265 -0.0233 1.0000 1.0000
-1.500 -0.0561 0.01320 0.00235 -0.0235 1.0000 1.0000
-1.250 -0.0284 0.01318 0.00204 -0.0237 1.0000 1.0000
-1.000 -0.0009 0.01317 0.00187 -0.0239 1.0000 1.0000
-0.750 0.0264 0.01318 0.00177 -0.0240 1.0000 1.0000
-0.500 0.0536 0.01319 0.00175 -0.0241 1.0000 1.0000
-0.250 0.0806 0.01323 0.00179 -0.0242 1.0000 1.0000
0.000 0.1076 0.01327 0.00191 -0.0242 1.0000 1.0000
0.250 0.1344 0.01333 0.00209 -0.0242 1.0000 1.0000
0.500 0.1613 0.01340 0.00243 -0.0241 1.0000 1.0000
0.750 0.1880 0.01348 0.00274 -0.0240 1.0000 1.0000
1.000 0.2146 0.01358 0.00314 -0.0239 1.0000 1.0000
1.250 0.2413 0.01370 0.00368 -0.0237 1.0000 1.0000
1.500 0.2682 0.01384 0.00446 -0.0234 1.0000 1.0000
1.750 0.3357 0.01972 0.00692 -0.0296 0.0601 1.0000
2.000 0.3633 0.02124 0.00856 -0.0294 0.0402 1.0000
2.250 0.3936 0.02311 0.01075 -0.0289 0.0358 1.0000
2.500 0.4236 0.02522 0.01320 -0.0282 0.0337 1.0000
2.750 0.4536 0.02761 0.01643 -0.0274 0.0333 1.0000
3.000 0.4830 0.03028 0.01962 -0.0268 0.0336 1.0000
3.250 0.5117 0.03327 0.02313 -0.0262 0.0344 1.0000
3.500 0.5393 0.03651 0.02689 -0.0258 0.0353 1.0000
3.750 0.5661 0.03984 0.03078 -0.0255 0.0349 1.0000
4.000 0.5920 0.04330 0.03477 -0.0254 0.0332 1.0000
4.250 0.6161 0.04695 0.03888 -0.0257 0.0310 1.0000
4.500 0.6385 0.05085 0.04316 -0.0262 0.0296 1.0000
4.750 0.6608 0.05527 0.04796 -0.0270 0.0305 1.0000
5.000 0.6816 0.06003 0.05305 -0.0283 0.0330 1.0000
5.250 0.6981 0.06493 0.05811 -0.0293 0.0365 1.0000
6.250 0.7734 0.08690 0.08099 -0.0415 0.0949 1.0000
6.500 0.7836 0.09187 0.08594 -0.0405 0.0917 1.0000
6.750 0.7878 0.09651 0.09066 -0.0480 0.0867 1.0000
7.000 0.7933 0.10101 0.09517 -0.0517 0.0828 1.0000
7.250 0.8002 0.10562 0.09978 -0.0522 0.0797 1.0000
7.500 0.8093 0.11171 0.10581 -0.0489 0.0776 1.0000
7.750 0.8067 0.11533 0.10941 -0.0567 0.0769 1.0000
8.000 0.8020 0.11868 0.11268 -0.0631 0.0745 1.0000
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Polar data table (+)
Polar graphs
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