NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 200,000 Max Cl/Cd: 32.1 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20503-il-200000-n5.txt Download as CSV file: xf-sc20503-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6397 0.10492 0.10137 0.0147 1.0000 0.0134
-8.500 -0.6353 0.10098 0.09745 0.0124 1.0000 0.0134
-8.250 -0.6308 0.09697 0.09348 0.0098 1.0000 0.0135
-8.000 -0.6234 0.09257 0.08909 0.0058 1.0000 0.0135
-7.750 -0.6127 0.08764 0.08417 0.0002 1.0000 0.0135
-7.500 -0.6000 0.08251 0.07902 -0.0054 1.0000 0.0135
-7.250 -0.5862 0.07748 0.07393 -0.0101 1.0000 0.0135
-7.000 -0.5712 0.07251 0.06888 -0.0144 1.0000 0.0135
-6.750 -0.5547 0.06762 0.06388 -0.0180 1.0000 0.0135
-6.500 -0.5368 0.06280 0.05894 -0.0213 1.0000 0.0135
-6.250 -0.5223 0.05551 0.05152 -0.0255 1.0000 0.0140
-6.000 -0.5036 0.04961 0.04541 -0.0287 1.0000 0.0144
-5.750 -0.4807 0.04476 0.04032 -0.0312 1.0000 0.0147
-5.500 -0.4540 0.04081 0.03609 -0.0328 1.0000 0.0144
-5.000 -0.4023 0.03237 0.02711 -0.0363 1.0000 0.0104
-4.750 -0.3714 0.02829 0.02260 -0.0377 1.0000 0.0091
-4.500 -0.3394 0.02459 0.01842 -0.0385 1.0000 0.0080
-4.250 -0.3074 0.02127 0.01458 -0.0389 1.0000 0.0073
-4.000 -0.2762 0.01849 0.01131 -0.0389 1.0000 0.0067
-3.750 -0.2465 0.01653 0.00874 -0.0386 1.0000 0.0058
-3.500 -0.2177 0.01472 0.00667 -0.0385 1.0000 0.0058
-3.250 -0.1889 0.01306 0.00484 -0.0386 1.0000 0.0061
-3.000 -0.1595 0.01184 0.00348 -0.0389 1.0000 0.0070
-2.750 -0.1312 0.01127 0.00285 -0.0391 1.0000 0.0119
-2.500 -0.1016 0.01048 0.00196 -0.0395 1.0000 0.0293
-2.250 -0.0698 0.00778 0.00164 -0.0421 1.0000 0.6479
-2.000 -0.0537 0.00740 0.00179 -0.0386 1.0000 0.8157
-1.750 -0.0347 0.00725 0.00169 -0.0360 1.0000 0.8643
-1.500 -0.0143 0.00710 0.00152 -0.0341 1.0000 0.8937
-1.250 0.0063 0.00695 0.00136 -0.0322 1.0000 0.9226
-1.000 0.0292 0.00678 0.00121 -0.0309 1.0000 0.9667
-0.750 0.0557 0.00674 0.00115 -0.0309 1.0000 1.0000
-0.500 0.0845 0.00677 0.00116 -0.0313 1.0000 1.0000
-0.250 0.1129 0.00680 0.00121 -0.0316 1.0000 1.0000
0.000 0.1412 0.00684 0.00130 -0.0319 1.0000 1.0000
0.250 0.1693 0.00689 0.00146 -0.0320 1.0000 1.0000
0.500 0.1972 0.00694 0.00163 -0.0322 1.0000 1.0000
0.750 0.2250 0.00701 0.00186 -0.0323 1.0000 1.0000
1.000 0.2838 0.01093 0.00240 -0.0389 0.0218 1.0000
1.250 0.3117 0.01154 0.00304 -0.0389 0.0091 1.0000
1.500 0.3393 0.01234 0.00394 -0.0387 0.0065 1.0000
1.750 0.3662 0.01368 0.00540 -0.0383 0.0058 1.0000
2.000 0.3933 0.01540 0.00728 -0.0378 0.0056 1.0000
2.250 0.4213 0.01723 0.00937 -0.0373 0.0056 1.0000
2.500 0.4505 0.01919 0.01193 -0.0365 0.0065 1.0000
2.750 0.4794 0.02188 0.01508 -0.0356 0.0071 1.0000
3.000 0.5080 0.02499 0.01868 -0.0346 0.0079 1.0000
3.250 0.5356 0.02837 0.02251 -0.0338 0.0088 1.0000
3.500 0.5620 0.03202 0.02658 -0.0331 0.0100 1.0000
3.750 0.5854 0.03633 0.03126 -0.0328 0.0117 1.0000
4.000 0.6060 0.04031 0.03544 -0.0329 0.0140 1.0000
4.250 0.6313 0.04352 0.03894 -0.0326 0.0144 1.0000
4.500 0.6522 0.04794 0.04364 -0.0328 0.0142 1.0000
4.750 0.6692 0.05353 0.04947 -0.0335 0.0138 1.0000
5.000 0.6821 0.06075 0.05688 -0.0349 0.0133 1.0000
5.250 0.7000 0.06540 0.06172 -0.0360 0.0133 1.0000
5.500 0.7166 0.07014 0.06663 -0.0375 0.0133 1.0000
5.750 0.7320 0.07500 0.07162 -0.0393 0.0133 1.0000
6.000 0.7460 0.07992 0.07666 -0.0415 0.0132 1.0000
6.250 0.7586 0.08490 0.08173 -0.0442 0.0132 1.0000
6.500 0.7697 0.08990 0.08681 -0.0473 0.0132 1.0000
6.750 0.7794 0.09490 0.09186 -0.0508 0.0132 1.0000
7.000 0.7875 0.09987 0.09686 -0.0547 0.0132 1.0000
7.250 0.7936 0.10473 0.10173 -0.0588 0.0132 1.0000
7.500 0.7962 0.10926 0.10625 -0.0626 0.0131 1.0000
7.750 0.7986 0.11368 0.11064 -0.0657 0.0131 1.0000
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Polar data table (+)
Polar graphs
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