RG-12 (rg12-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 50,000 Max Cl/Cd: 32.94 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12-il-50000.txt Download as CSV file: xf-rg12-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RG-12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4929 0.10431 0.09750 -0.0091 1.0000 0.2716
-8.500 -0.4887 0.10108 0.09425 -0.0085 1.0000 0.2844
-8.250 -0.4841 0.09770 0.09093 -0.0078 1.0000 0.2982
-8.000 -0.4888 0.09507 0.08839 -0.0071 1.0000 0.3128
-7.750 -0.4646 0.09062 0.08392 -0.0046 1.0000 0.3378
-7.500 -0.4803 0.08889 0.08234 -0.0035 1.0000 0.3549
-7.250 -0.4621 0.08453 0.07798 -0.0020 1.0000 0.3719
-6.750 -0.5631 0.06301 0.05616 -0.0339 1.0000 0.1460
-6.500 -0.5506 0.05701 0.05003 -0.0337 1.0000 0.1263
-6.250 -0.5459 0.05149 0.04402 -0.0339 1.0000 0.1142
-6.000 -0.5390 0.04631 0.03795 -0.0333 1.0000 0.1051
-5.750 -0.5246 0.04284 0.03393 -0.0320 1.0000 0.1044
-5.500 -0.5081 0.03972 0.03092 -0.0309 1.0000 0.1096
-5.250 -0.4901 0.03663 0.02732 -0.0297 1.0000 0.1122
-5.000 -0.4694 0.03354 0.02370 -0.0283 1.0000 0.1140
-4.750 -0.4468 0.03079 0.02033 -0.0269 1.0000 0.1189
-4.500 -0.4255 0.02865 0.01813 -0.0257 1.0000 0.1344
-4.250 -0.4022 0.02649 0.01591 -0.0243 1.0000 0.1527
-4.000 -0.3793 0.02461 0.01400 -0.0228 1.0000 0.1859
-3.750 -0.3573 0.02272 0.01244 -0.0212 1.0000 0.2381
-3.500 -0.3372 0.02053 0.01093 -0.0193 1.0000 0.3369
-3.250 -0.3359 0.01793 0.01064 -0.0121 1.0000 0.6203
-3.000 -0.0978 0.01980 0.01091 -0.0365 1.0000 1.0000
-2.750 -0.0929 0.01932 0.01029 -0.0342 1.0000 1.0000
-2.500 -0.0879 0.01896 0.00975 -0.0317 1.0000 1.0000
-2.250 -0.0835 0.01866 0.00934 -0.0289 1.0000 1.0000
-2.000 -0.0801 0.01843 0.00901 -0.0258 1.0000 1.0000
-1.750 -0.0779 0.01825 0.00873 -0.0224 1.0000 1.0000
-1.500 -0.0769 0.01810 0.00850 -0.0188 1.0000 1.0000
-1.250 -0.0762 0.01798 0.00830 -0.0152 1.0000 1.0000
-1.000 -0.0745 0.01791 0.00814 -0.0117 1.0000 1.0000
-0.750 -0.0702 0.01790 0.00802 -0.0088 1.0000 1.0000
-0.500 -0.0615 0.01798 0.00794 -0.0066 1.0000 1.0000
-0.250 -0.0493 0.01813 0.00797 -0.0050 1.0000 1.0000
0.000 -0.0351 0.01835 0.00807 -0.0039 1.0000 1.0000
0.250 -0.0197 0.01863 0.00825 -0.0030 1.0000 1.0000
0.500 -0.0036 0.01898 0.00851 -0.0023 1.0000 1.0000
0.750 0.0127 0.01939 0.00882 -0.0017 1.0000 1.0000
1.000 0.0292 0.01986 0.00923 -0.0013 1.0000 1.0000
1.250 0.0456 0.02040 0.00972 -0.0010 1.0000 1.0000
1.500 0.0618 0.02101 0.01030 -0.0008 1.0000 1.0000
1.750 0.0777 0.02170 0.01096 -0.0007 1.0000 1.0000
2.000 0.1295 0.02304 0.01233 -0.0074 0.9839 1.0000
2.250 0.1877 0.02423 0.01358 -0.0147 0.9610 1.0000
2.500 0.2437 0.02520 0.01466 -0.0212 0.9377 1.0000
2.750 0.3032 0.02597 0.01556 -0.0278 0.9144 1.0000
3.000 0.3555 0.02645 0.01622 -0.0327 0.8896 1.0000
3.250 0.4064 0.02675 0.01674 -0.0368 0.8639 1.0000
3.500 0.4608 0.02677 0.01699 -0.0408 0.8381 1.0000
3.750 0.5187 0.02642 0.01693 -0.0446 0.8118 1.0000
4.000 0.5707 0.02588 0.01671 -0.0468 0.7841 1.0000
4.250 0.6170 0.02525 0.01633 -0.0475 0.7544 1.0000
4.500 0.6601 0.02452 0.01581 -0.0472 0.7224 1.0000
4.750 0.6916 0.02420 0.01569 -0.0454 0.6866 1.0000
5.000 0.7229 0.02385 0.01541 -0.0433 0.6485 1.0000
5.250 0.7490 0.02377 0.01535 -0.0408 0.6067 1.0000
5.500 0.7715 0.02392 0.01547 -0.0380 0.5613 1.0000
5.750 0.7937 0.02414 0.01557 -0.0351 0.5127 1.0000
6.000 0.8123 0.02466 0.01602 -0.0322 0.4605 1.0000
6.250 0.8298 0.02538 0.01653 -0.0292 0.4058 1.0000
6.500 0.8460 0.02637 0.01726 -0.0264 0.3501 1.0000
6.750 0.8616 0.02768 0.01829 -0.0237 0.2964 1.0000
7.000 0.8776 0.02922 0.01949 -0.0214 0.2480 1.0000
7.250 0.8951 0.03119 0.02128 -0.0194 0.2072 1.0000
7.500 0.9128 0.03344 0.02348 -0.0176 0.1750 1.0000
7.750 0.9313 0.03581 0.02578 -0.0160 0.1494 1.0000
8.000 0.9500 0.03884 0.02921 -0.0144 0.1333 1.0000
8.250 0.9654 0.04163 0.03224 -0.0127 0.1193 1.0000
8.500 0.9838 0.04514 0.03584 -0.0115 0.1103 1.0000
8.750 0.9897 0.04925 0.04069 -0.0090 0.1073 1.0000
9.000 0.9925 0.05358 0.04558 -0.0067 0.1052 1.0000
9.250 0.9945 0.05750 0.04986 -0.0048 0.1020 1.0000
9.500 1.0009 0.06136 0.05380 -0.0035 0.0967 1.0000
9.750 0.9898 0.06578 0.05863 -0.0015 0.0963 1.0000
10.000 0.9763 0.07034 0.06349 0.0001 0.0965 1.0000
10.250 0.9600 0.07498 0.06833 0.0013 0.0969 1.0000
10.500 0.9458 0.07960 0.07306 0.0021 0.0975 1.0000
10.750 0.8853 0.08812 0.08181 -0.0017 0.1099 1.0000
11.000 0.8728 0.09447 0.08817 -0.0043 0.1108 1.0000
11.250 0.8382 0.10704 0.10070 -0.0133 0.1245 1.0000
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Polar data table (+)
Polar graphs
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