NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 100,000 Max Cl/Cd: 26.54 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20503-il-100000.txt Download as CSV file: xf-sc20503-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6698 0.11912 0.11421 0.0188 1.0000 0.0472
-9.250 -0.6689 0.11616 0.11131 0.0147 1.0000 0.0475
-9.000 -0.6680 0.11297 0.10818 0.0104 1.0000 0.0477
-8.750 -0.6643 0.10921 0.10446 0.0046 1.0000 0.0479
-8.500 -0.6533 0.10168 0.09690 0.0151 1.0000 0.0513
-8.250 -0.6490 0.09794 0.09307 0.0138 1.0000 0.0534
-8.000 -0.6454 0.09418 0.08936 0.0114 1.0000 0.0554
-7.750 -0.6384 0.08990 0.08511 0.0061 1.0000 0.0578
-7.500 -0.6245 0.08485 0.08002 -0.0058 1.0000 0.0600
-7.250 -0.6063 0.08078 0.07565 -0.0180 1.0000 0.0609
-7.000 -0.6047 0.07472 0.06989 -0.0109 1.0000 0.0640
-6.750 -0.5913 0.07051 0.06564 -0.0132 1.0000 0.0687
-6.500 -0.5640 0.06541 0.06007 -0.0251 1.0000 0.0746
-6.250 -0.5557 0.06070 0.05560 -0.0220 1.0000 0.0792
-6.000 -0.5309 0.05583 0.05040 -0.0280 1.0000 0.0890
-5.750 -0.5079 0.05178 0.04608 -0.0311 1.0000 0.1016
-5.500 -0.4878 0.04758 0.04182 -0.0325 1.0000 0.1156
-5.250 -0.4651 0.04429 0.03838 -0.0339 1.0000 0.1379
-4.250 -0.3250 0.02758 0.01947 -0.0401 1.0000 0.0707
-4.000 -0.2890 0.02454 0.01553 -0.0395 1.0000 0.0492
-3.750 -0.2605 0.02190 0.01253 -0.0398 1.0000 0.0549
-3.500 -0.2301 0.01961 0.00982 -0.0391 1.0000 0.0517
-3.250 -0.2013 0.01769 0.00766 -0.0382 1.0000 0.0503
-3.000 -0.1738 0.01591 0.00592 -0.0376 1.0000 0.0536
-2.750 -0.1457 0.01446 0.00452 -0.0375 1.0000 0.0703
-2.500 -0.1187 0.01056 0.00317 -0.0378 1.0000 0.6557
-2.250 -0.1325 0.00950 0.00286 -0.0244 1.0000 1.0000
-2.000 -0.1026 0.00945 0.00236 -0.0251 1.0000 1.0000
-1.750 -0.0732 0.00941 0.00204 -0.0258 1.0000 1.0000
-1.500 -0.0441 0.00938 0.00181 -0.0264 1.0000 1.0000
-1.250 -0.0154 0.00938 0.00161 -0.0268 1.0000 1.0000
-1.000 0.0130 0.00938 0.00150 -0.0272 1.0000 1.0000
-0.750 0.0412 0.00939 0.00145 -0.0275 1.0000 1.0000
-0.500 0.0691 0.00942 0.00144 -0.0277 1.0000 1.0000
-0.250 0.0969 0.00945 0.00149 -0.0279 1.0000 1.0000
0.000 0.1245 0.00949 0.00160 -0.0281 1.0000 1.0000
0.250 0.1520 0.00955 0.00175 -0.0281 1.0000 1.0000
0.500 0.1794 0.00961 0.00201 -0.0282 1.0000 1.0000
0.750 0.2067 0.00969 0.00228 -0.0282 1.0000 1.0000
1.000 0.2340 0.00977 0.00265 -0.0281 1.0000 1.0000
1.250 0.2619 0.00987 0.00334 -0.0278 1.0000 1.0000
1.500 0.3277 0.01563 0.00568 -0.0339 0.0552 1.0000
1.750 0.3548 0.01732 0.00733 -0.0332 0.0503 1.0000
2.000 0.3839 0.01932 0.00941 -0.0325 0.0498 1.0000
2.250 0.4149 0.02163 0.01212 -0.0314 0.0550 1.0000
2.500 0.4449 0.02405 0.01494 -0.0307 0.0558 1.0000
2.750 0.4740 0.02693 0.01843 -0.0301 0.0579 1.0000
3.000 0.5549 0.03246 0.02657 -0.0314 0.3045 1.0000
3.250 0.5710 0.03546 0.02953 -0.0291 0.2460 1.0000
3.750 0.6076 0.04144 0.03555 -0.0276 0.1553 1.0000
4.000 0.5909 0.02923 0.02407 -0.0232 0.1315 1.0000
4.250 0.6072 0.03324 0.02811 -0.0229 0.1146 1.0000
4.750 0.6813 0.05834 0.05275 -0.0283 0.0866 1.0000
5.250 0.7216 0.06578 0.06101 -0.0327 0.0707 1.0000
5.500 0.7396 0.07000 0.06544 -0.0351 0.0642 1.0000
5.750 0.7467 0.07575 0.07096 -0.0327 0.0606 1.0000
6.000 0.7609 0.08062 0.07612 -0.0371 0.0592 1.0000
6.250 0.7782 0.08507 0.08082 -0.0448 0.0558 1.0000
6.500 0.7881 0.08990 0.08570 -0.0488 0.0531 1.0000
6.750 0.7956 0.09454 0.09047 -0.0516 0.0508 1.0000
7.000 0.8013 0.09906 0.09499 -0.0498 0.0484 1.0000
7.250 0.8036 0.10649 0.10229 -0.0452 0.0469 1.0000
7.500 0.8092 0.11075 0.10662 -0.0509 0.0467 1.0000
7.750 0.8117 0.11491 0.11080 -0.0572 0.0465 1.0000
8.000 0.8115 0.11878 0.11462 -0.0627 0.0463 1.0000
8.250 0.8113 0.12239 0.11819 -0.0675 0.0458 1.0000
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Polar data table (+)
Polar graphs
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