NASA SC(2)-0503 AIRFOIL (sc20503-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0503 AIRFOIL (sc20503-il) Reynolds number: 500,000 Max Cl/Cd: 35.25 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20503-il-500000-n5.txt Download as CSV file: xf-sc20503-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6410 0.10227 0.09999 0.0177 1.0000 0.0052
-8.500 -0.6368 0.09832 0.09606 0.0156 1.0000 0.0052
-8.250 -0.6327 0.09437 0.09213 0.0133 1.0000 0.0052
-8.000 -0.6280 0.09030 0.08808 0.0104 1.0000 0.0052
-7.750 -0.6184 0.08557 0.08336 0.0053 1.0000 0.0052
-7.500 -0.6056 0.08032 0.07811 -0.0012 1.0000 0.0052
-7.250 -0.5908 0.07491 0.07266 -0.0075 1.0000 0.0052
-7.000 -0.5746 0.06961 0.06731 -0.0128 1.0000 0.0052
-6.750 -0.5569 0.06442 0.06204 -0.0174 1.0000 0.0052
-6.500 -0.5378 0.05935 0.05686 -0.0213 1.0000 0.0052
-6.250 -0.5188 0.05294 0.05033 -0.0255 1.0000 0.0053
-6.000 -0.4983 0.04617 0.04334 -0.0295 1.0000 0.0056
-5.750 -0.4747 0.04067 0.03761 -0.0323 1.0000 0.0058
-5.500 -0.4488 0.03598 0.03266 -0.0345 1.0000 0.0059
-5.250 -0.4210 0.03180 0.02819 -0.0362 1.0000 0.0061
-5.000 -0.3914 0.02796 0.02404 -0.0374 1.0000 0.0061
-4.500 -0.3328 0.02292 0.01849 -0.0385 1.0000 0.0049
-4.250 -0.3003 0.01892 0.01402 -0.0397 1.0000 0.0044
-4.000 -0.2686 0.01598 0.01064 -0.0403 1.0000 0.0041
-3.750 -0.2380 0.01359 0.00776 -0.0404 1.0000 0.0037
-3.500 -0.2081 0.01162 0.00552 -0.0404 1.0000 0.0035
-3.250 -0.1782 0.01008 0.00379 -0.0407 1.0000 0.0033
-3.000 -0.1479 0.00897 0.00253 -0.0412 1.0000 0.0034
-2.750 -0.1185 0.00831 0.00171 -0.0415 1.0000 0.0037
-2.500 -0.0904 0.00798 0.00126 -0.0415 1.0000 0.0045
-2.250 -0.0631 0.00777 0.00105 -0.0414 1.0000 0.0105
-2.000 -0.0309 0.00646 0.00084 -0.0435 1.0000 0.3233
-1.750 0.0000 0.00530 0.00086 -0.0450 1.0000 0.6723
-1.500 0.0264 0.00512 0.00090 -0.0446 1.0000 0.7486
-1.250 0.0526 0.00504 0.00091 -0.0442 1.0000 0.7788
-1.000 0.0786 0.00498 0.00094 -0.0438 1.0000 0.8043
-0.750 0.1048 0.00495 0.00097 -0.0434 1.0000 0.8240
-0.500 0.1308 0.00492 0.00102 -0.0429 1.0000 0.8396
-0.250 0.1569 0.00490 0.00109 -0.0425 1.0000 0.8542
0.250 0.2300 0.00714 0.00115 -0.0464 0.3111 0.8763
0.500 0.2537 0.00839 0.00136 -0.0462 0.0116 0.8892
0.750 0.2794 0.00855 0.00154 -0.0456 0.0044 0.9025
1.000 0.3044 0.00877 0.00191 -0.0448 0.0036 0.9190
1.500 0.3543 0.01005 0.00355 -0.0428 0.0032 1.0000
1.750 0.3815 0.01142 0.00507 -0.0423 0.0033 1.0000
2.000 0.4092 0.01320 0.00706 -0.0417 0.0035 1.0000
2.250 0.4376 0.01538 0.00953 -0.0410 0.0038 1.0000
2.500 0.4657 0.01785 0.01252 -0.0403 0.0041 1.0000
2.750 0.4932 0.02089 0.01596 -0.0395 0.0045 1.0000
3.000 0.5177 0.02530 0.02082 -0.0388 0.0052 1.0000
3.250 0.5464 0.02601 0.02165 -0.0382 0.0058 1.0000
3.500 0.5731 0.02916 0.02512 -0.0373 0.0060 1.0000
3.750 0.5980 0.03270 0.02896 -0.0367 0.0060 1.0000
4.000 0.6214 0.03653 0.03307 -0.0364 0.0058 1.0000
4.250 0.6432 0.04085 0.03765 -0.0363 0.0056 1.0000
4.500 0.6630 0.04602 0.04308 -0.0365 0.0054 1.0000
4.750 0.6796 0.05286 0.05019 -0.0374 0.0052 1.0000
5.000 0.6976 0.05849 0.05597 -0.0385 0.0051 1.0000
5.250 0.7160 0.06332 0.06095 -0.0398 0.0051 1.0000
5.500 0.7332 0.06827 0.06603 -0.0416 0.0051 1.0000
5.750 0.7490 0.07335 0.07121 -0.0439 0.0051 1.0000
6.000 0.7632 0.07849 0.07643 -0.0467 0.0051 1.0000
6.250 0.7759 0.08368 0.08170 -0.0500 0.0051 1.0000
6.500 0.7868 0.08888 0.08694 -0.0537 0.0051 1.0000
6.750 0.7959 0.09404 0.09214 -0.0578 0.0051 1.0000
7.000 0.8032 0.09913 0.09724 -0.0623 0.0051 1.0000
7.250 0.8061 0.10385 0.10196 -0.0664 0.0051 1.0000
7.500 0.8073 0.10829 0.10638 -0.0697 0.0051 1.0000
7.750 0.8090 0.11265 0.11073 -0.0722 0.0051 1.0000
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Polar data table (+)
Polar graphs
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