NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il) Reynolds number: 500,000 Max Cl/Cd: 55.8 at α=-0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20706-il-500000-n5.txt Download as CSV file: xf-sc20706-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0706 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6307 0.08261 0.08031 -0.0175 1.0000 0.0070
-9.750 -0.6426 0.07737 0.07515 -0.0193 1.0000 0.0069
-9.500 -0.6583 0.07190 0.06974 -0.0215 1.0000 0.0069
-9.250 -0.6719 0.06013 0.05791 -0.0347 1.0000 0.0068
-9.000 -0.6762 0.05089 0.04845 -0.0412 1.0000 0.0068
-8.750 -0.6702 0.04177 0.03895 -0.0465 1.0000 0.0069
-8.500 -0.6524 0.03394 0.03063 -0.0509 1.0000 0.0072
-8.250 -0.6262 0.02790 0.02403 -0.0547 1.0000 0.0075
-8.000 -0.5991 0.02536 0.02118 -0.0565 1.0000 0.0079
-7.750 -0.5707 0.02301 0.01847 -0.0581 1.0000 0.0085
-7.500 -0.5382 0.01962 0.01457 -0.0605 1.0000 0.0087
-7.250 -0.5067 0.01732 0.01191 -0.0621 1.0000 0.0090
-7.000 -0.4760 0.01575 0.01007 -0.0632 1.0000 0.0094
-6.750 -0.4458 0.01460 0.00873 -0.0642 1.0000 0.0099
-6.500 -0.4159 0.01377 0.00776 -0.0650 1.0000 0.0104
-6.250 -0.3865 0.01312 0.00698 -0.0657 1.0000 0.0107
-6.000 -0.3524 0.01199 0.00572 -0.0676 1.0000 0.0116
-5.750 -0.3218 0.01148 0.00517 -0.0685 1.0000 0.0127
-5.500 -0.2924 0.01117 0.00483 -0.0692 1.0000 0.0142
-5.250 -0.2613 0.01077 0.00438 -0.0701 1.0000 0.0157
-5.000 -0.2308 0.01048 0.00400 -0.0709 1.0000 0.0172
-4.750 -0.1983 0.01006 0.00357 -0.0722 1.0000 0.0222
-4.500 -0.1686 0.00988 0.00335 -0.0728 1.0000 0.0263
-4.250 -0.1382 0.00967 0.00316 -0.0735 1.0000 0.0347
-4.000 -0.1071 0.00942 0.00299 -0.0745 1.0000 0.0566
-3.750 -0.0752 0.00914 0.00286 -0.0757 1.0000 0.0944
-3.500 -0.0417 0.00879 0.00274 -0.0774 1.0000 0.1629
-3.250 -0.0050 0.00829 0.00263 -0.0799 1.0000 0.2766
-3.000 0.0378 0.00752 0.00253 -0.0841 1.0000 0.4768
-2.750 0.0708 0.00731 0.00260 -0.0855 1.0000 0.5645
-2.500 0.1006 0.00726 0.00267 -0.0860 1.0000 0.6053
-2.250 0.1296 0.00725 0.00276 -0.0862 1.0000 0.6368
-2.000 0.1578 0.00728 0.00285 -0.0863 1.0000 0.6580
-1.750 0.1859 0.00732 0.00294 -0.0864 1.0000 0.6728
-1.500 0.2346 0.00708 0.00276 -0.0910 0.9935 0.6871
-1.250 0.2774 0.00683 0.00258 -0.0942 0.9857 0.6999
-1.000 0.3152 0.00663 0.00245 -0.0963 0.9774 0.7096
-0.500 0.4068 0.00729 0.00175 -0.1030 0.5863 0.7244
-0.250 0.4281 0.00842 0.00203 -0.1020 0.3657 0.7308
0.000 0.4523 0.00925 0.00226 -0.1015 0.2037 0.7374
0.250 0.4783 0.00980 0.00248 -0.1013 0.1124 0.7439
0.500 0.5050 0.01018 0.00270 -0.1011 0.0662 0.7500
1.000 0.5591 0.01078 0.00318 -0.1008 0.0279 0.7625
1.250 0.5865 0.01104 0.00346 -0.1006 0.0230 0.7688
1.500 0.6136 0.01131 0.00376 -0.1004 0.0189 0.7740
1.750 0.6401 0.01177 0.00428 -0.1000 0.0153 0.7798
2.000 0.6668 0.01215 0.00475 -0.0997 0.0140 0.7857
2.250 0.6931 0.01263 0.00532 -0.0992 0.0130 0.7917
2.750 0.7453 0.01365 0.00648 -0.0983 0.0114 0.8033
3.000 0.7714 0.01415 0.00702 -0.0979 0.0105 0.8092
3.250 0.7961 0.01511 0.00810 -0.0971 0.0099 0.8141
3.500 0.8202 0.01646 0.00965 -0.0962 0.0095 0.8193
4.000 0.8709 0.01838 0.01193 -0.0949 0.0089 0.8298
4.250 0.8956 0.01982 0.01362 -0.0940 0.0085 0.8353
4.500 0.9193 0.02180 0.01593 -0.0929 0.0082 0.8402
4.750 0.9409 0.02463 0.01921 -0.0913 0.0079 0.8451
5.000 0.9598 0.02854 0.02368 -0.0892 0.0077 0.8505
5.250 0.9780 0.03182 0.02740 -0.0873 0.0072 0.8554
5.500 0.9941 0.03557 0.03155 -0.0853 0.0068 0.8608
5.750 1.0046 0.04157 0.03804 -0.0825 0.0066 0.8660
6.000 1.0145 0.04667 0.04352 -0.0802 0.0064 0.8708
6.250 1.0219 0.05214 0.04931 -0.0782 0.0062 0.8763
6.500 1.0269 0.05759 0.05504 -0.0765 0.0060 0.8817
6.750 1.0255 0.06433 0.06206 -0.0752 0.0059 0.8875
7.000 1.0186 0.07183 0.06980 -0.0746 0.0058 0.8938
7.250 1.0101 0.07885 0.07700 -0.0750 0.0058 0.9008
7.500 0.9996 0.08560 0.08387 -0.0765 0.0058 0.9089
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Polar data table (+)
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