RG-12 (rg12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 500,000 Max Cl/Cd: 72.25 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12-il-500000-n5.txt Download as CSV file: xf-rg12-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7215 0.04472 0.04219 -0.0471 1.0000 0.0050
-9.500 -0.7422 0.03991 0.03708 -0.0449 1.0000 0.0050
-9.250 -0.7531 0.03599 0.03285 -0.0423 1.0000 0.0050
-9.000 -0.7575 0.03249 0.02902 -0.0397 1.0000 0.0051
-8.750 -0.7556 0.02947 0.02567 -0.0372 1.0000 0.0052
-8.500 -0.7454 0.02774 0.02374 -0.0354 1.0000 0.0053
-8.250 -0.7330 0.02619 0.02200 -0.0336 1.0000 0.0055
-8.000 -0.7163 0.02551 0.02121 -0.0323 1.0000 0.0058
-7.750 -0.6983 0.02361 0.01903 -0.0315 0.9994 0.0060
-7.500 -0.6705 0.02156 0.01667 -0.0325 0.9972 0.0062
-7.250 -0.6419 0.01958 0.01436 -0.0335 0.9951 0.0063
-7.000 -0.6133 0.01795 0.01247 -0.0342 0.9930 0.0064
-6.750 -0.5849 0.01663 0.01095 -0.0348 0.9903 0.0065
-6.500 -0.5552 0.01551 0.00966 -0.0356 0.9876 0.0068
-6.250 -0.5242 0.01455 0.00853 -0.0365 0.9852 0.0071
-6.000 -0.4918 0.01372 0.00759 -0.0378 0.9832 0.0075
-5.750 -0.4634 0.01306 0.00683 -0.0381 0.9794 0.0078
-5.500 -0.4335 0.01249 0.00617 -0.0387 0.9754 0.0081
-5.250 -0.4022 0.01173 0.00531 -0.0397 0.9722 0.0089
-5.000 -0.3688 0.01122 0.00474 -0.0410 0.9699 0.0098
-4.750 -0.3420 0.01085 0.00433 -0.0409 0.9636 0.0110
-4.250 -0.2763 0.01005 0.00350 -0.0432 0.9563 0.0193
-4.000 -0.2483 0.00969 0.00318 -0.0433 0.9486 0.0323
-3.750 -0.2144 0.00935 0.00288 -0.0447 0.9438 0.0482
-3.500 -0.1838 0.00901 0.00263 -0.0454 0.9359 0.0708
-3.250 -0.1500 0.00860 0.00237 -0.0469 0.9294 0.1118
-3.000 -0.1195 0.00818 0.00215 -0.0477 0.9191 0.1658
-2.750 -0.0882 0.00785 0.00196 -0.0485 0.9079 0.2132
-2.500 -0.0581 0.00753 0.00176 -0.0492 0.8948 0.2667
-2.250 -0.0299 0.00714 0.00160 -0.0494 0.8798 0.3459
-2.000 -0.0031 0.00675 0.00145 -0.0494 0.8636 0.4333
-1.750 0.0226 0.00639 0.00133 -0.0490 0.8463 0.5246
-1.500 0.0473 0.00606 0.00126 -0.0484 0.8281 0.6183
-1.250 0.0726 0.00595 0.00128 -0.0476 0.8092 0.6873
-1.000 0.0987 0.00596 0.00128 -0.0471 0.7901 0.7209
-0.750 0.1250 0.00600 0.00128 -0.0466 0.7701 0.7426
-0.500 0.1512 0.00607 0.00127 -0.0461 0.7494 0.7587
-0.250 0.1775 0.00613 0.00127 -0.0456 0.7284 0.7722
0.250 0.2296 0.00630 0.00130 -0.0446 0.6843 0.7953
0.500 0.2557 0.00640 0.00132 -0.0441 0.6619 0.8049
0.750 0.2815 0.00650 0.00136 -0.0436 0.6389 0.8148
1.000 0.3072 0.00661 0.00140 -0.0430 0.6156 0.8246
1.250 0.3329 0.00673 0.00146 -0.0425 0.5920 0.8343
1.500 0.3585 0.00686 0.00151 -0.0419 0.5678 0.8440
1.750 0.3838 0.00698 0.00158 -0.0413 0.5427 0.8524
2.000 0.4095 0.00713 0.00165 -0.0409 0.5171 0.8602
2.250 0.4348 0.00728 0.00175 -0.0403 0.4907 0.8668
2.750 0.4859 0.00762 0.00193 -0.0394 0.4380 0.8787
3.000 0.5113 0.00781 0.00205 -0.0389 0.4118 0.8852
3.250 0.5363 0.00800 0.00217 -0.0384 0.3840 0.8917
3.500 0.5611 0.00823 0.00233 -0.0378 0.3541 0.8994
3.750 0.5855 0.00846 0.00248 -0.0372 0.3248 0.9072
4.000 0.6098 0.00870 0.00264 -0.0365 0.2957 0.9164
4.250 0.6338 0.00895 0.00282 -0.0358 0.2673 0.9273
4.500 0.6583 0.00922 0.00304 -0.0352 0.2389 0.9395
4.750 0.6849 0.00951 0.00326 -0.0351 0.2125 0.9531
5.000 0.7141 0.00989 0.00352 -0.0356 0.1801 0.9686
5.250 0.7456 0.01032 0.00382 -0.0368 0.1467 0.9877
5.500 0.7715 0.01082 0.00416 -0.0368 0.1128 1.0000
5.750 0.7954 0.01125 0.00451 -0.0363 0.0897 1.0000
6.000 0.8194 0.01166 0.00485 -0.0358 0.0733 1.0000
6.250 0.8436 0.01207 0.00521 -0.0353 0.0598 1.0000
6.750 0.8912 0.01295 0.00603 -0.0342 0.0367 1.0000
7.000 0.9143 0.01346 0.00649 -0.0336 0.0260 1.0000
7.250 0.9375 0.01395 0.00699 -0.0330 0.0200 1.0000
7.500 0.9609 0.01442 0.00750 -0.0324 0.0162 1.0000
7.750 0.9834 0.01497 0.00805 -0.0316 0.0129 1.0000
8.000 1.0062 0.01548 0.00861 -0.0310 0.0107 1.0000
8.250 1.0284 0.01604 0.00921 -0.0302 0.0090 1.0000
8.500 1.0494 0.01673 0.00996 -0.0292 0.0076 1.0000
8.750 1.0709 0.01734 0.01066 -0.0284 0.0068 1.0000
9.000 1.0917 0.01800 0.01140 -0.0274 0.0060 1.0000
9.250 1.1116 0.01872 0.01222 -0.0263 0.0053 1.0000
9.500 1.1294 0.01964 0.01325 -0.0250 0.0048 1.0000
9.750 1.1437 0.02088 0.01462 -0.0231 0.0045 1.0000
10.000 1.1604 0.02179 0.01566 -0.0217 0.0043 1.0000
10.250 1.1753 0.02283 0.01683 -0.0200 0.0042 1.0000
10.500 1.1885 0.02395 0.01808 -0.0181 0.0041 1.0000
10.750 1.1996 0.02514 0.01942 -0.0160 0.0040 1.0000
11.000 1.2066 0.02640 0.02083 -0.0132 0.0038 1.0000
11.250 1.2124 0.02771 0.02229 -0.0104 0.0038 1.0000
11.500 1.2165 0.02915 0.02388 -0.0077 0.0036 1.0000
11.750 1.2205 0.03061 0.02552 -0.0052 0.0035 1.0000
12.000 1.2217 0.03234 0.02741 -0.0029 0.0034 1.0000
12.250 1.2251 0.03392 0.02913 -0.0011 0.0033 1.0000
12.500 1.2256 0.03585 0.03120 0.0006 0.0032 1.0000
12.750 1.2246 0.03806 0.03357 0.0018 0.0031 1.0000
13.000 1.2207 0.04075 0.03642 0.0027 0.0031 1.0000
13.250 1.2128 0.04413 0.03998 0.0029 0.0031 1.0000
13.500 1.2075 0.04752 0.04352 0.0025 0.0030 1.0000
13.750 1.1921 0.05260 0.04883 0.0011 0.0031 1.0000
14.000 1.1894 0.05629 0.05262 -0.0006 0.0030 1.0000
14.250 1.1774 0.06174 0.05824 -0.0033 0.0029 1.0000
14.500 1.1635 0.06797 0.06464 -0.0067 0.0029 1.0000
14.750 1.1454 0.07536 0.07222 -0.0110 0.0029 1.0000
15.000 1.1271 0.08330 0.08031 -0.0158 0.0029 1.0000
15.250 1.1052 0.09238 0.08956 -0.0212 0.0029 1.0000
15.500 1.0752 0.10377 0.10114 -0.0279 0.0031 1.0000
15.750 1.0449 0.11587 0.11341 -0.0349 0.0031 1.0000
16.000 1.0150 0.12859 0.12628 -0.0421 0.0032 1.0000
16.250 0.9629 0.14865 0.14650 -0.0529 0.0035 1.0000
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Polar data table (+)
Polar graphs
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