RG-12 (rg12-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 100,000 Max Cl/Cd: 48.85 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12-il-100000.txt Download as CSV file: xf-rg12-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4959 0.10320 0.09819 -0.0205 1.0000 0.1016
-9.250 -0.5196 0.09973 0.09486 -0.0272 1.0000 0.1041
-9.000 -0.5156 0.09487 0.09004 -0.0269 1.0000 0.1059
-8.750 -0.4974 0.09189 0.08703 -0.0237 1.0000 0.1102
-8.500 -0.5018 0.08835 0.08356 -0.0253 1.0000 0.1142
-8.250 -0.5318 0.08426 0.07962 -0.0312 1.0000 0.1170
-8.000 -0.5758 0.08094 0.07618 -0.0368 1.0000 0.1182
-7.750 -0.5318 0.07658 0.07203 -0.0302 1.0000 0.1226
-7.500 -0.5371 0.07312 0.06858 -0.0310 1.0000 0.1278
-7.250 -0.5609 0.06860 0.06395 -0.0342 1.0000 0.1332
-7.000 -0.5438 0.06592 0.06138 -0.0312 1.0000 0.1392
-6.750 -0.5499 0.06221 0.05760 -0.0315 1.0000 0.1490
-6.500 -0.5617 0.04943 0.04337 -0.0347 1.0000 0.0773
-6.250 -0.5509 0.04239 0.03608 -0.0333 1.0000 0.0625
-6.000 -0.5395 0.03868 0.03202 -0.0317 1.0000 0.0617
-5.750 -0.5256 0.03510 0.02806 -0.0301 1.0000 0.0601
-5.500 -0.5092 0.03137 0.02379 -0.0283 1.0000 0.0572
-5.250 -0.4897 0.02813 0.01992 -0.0265 1.0000 0.0555
-5.000 -0.4684 0.02575 0.01714 -0.0250 1.0000 0.0558
-4.750 -0.4462 0.02379 0.01489 -0.0236 1.0000 0.0578
-4.500 -0.4233 0.02210 0.01297 -0.0222 1.0000 0.0617
-4.250 -0.4017 0.02054 0.01139 -0.0210 1.0000 0.0702
-4.000 -0.3802 0.01920 0.01008 -0.0197 1.0000 0.0859
-3.750 -0.3591 0.01794 0.00890 -0.0184 1.0000 0.1183
-3.500 -0.3391 0.01660 0.00794 -0.0173 1.0000 0.1665
-3.250 -0.3201 0.01499 0.00713 -0.0161 1.0000 0.2820
-3.000 -0.3089 0.01317 0.00695 -0.0130 1.0000 0.5825
-2.750 -0.3023 0.01317 0.00745 -0.0070 1.0000 0.7611
-2.500 -0.2947 0.01335 0.00767 -0.0016 1.0000 0.8325
-2.250 -0.2863 0.01350 0.00780 0.0038 1.0000 0.8884
-2.000 -0.2458 0.01385 0.00798 0.0032 1.0000 0.9475
-1.750 -0.1103 0.01442 0.00794 -0.0158 1.0000 0.9905
-1.500 -0.0722 0.01435 0.00769 -0.0191 1.0000 1.0000
-1.250 -0.0794 0.01423 0.00754 -0.0144 1.0000 1.0000
-1.000 -0.0869 0.01412 0.00740 -0.0098 1.0000 1.0000
-0.750 -0.0901 0.01407 0.00728 -0.0060 1.0000 1.0000
-0.500 -0.0832 0.01415 0.00727 -0.0038 1.0000 1.0000
-0.250 -0.0299 0.01464 0.00760 -0.0098 0.9891 1.0000
0.000 0.0217 0.01504 0.00790 -0.0153 0.9777 1.0000
0.250 0.0724 0.01534 0.00811 -0.0205 0.9660 1.0000
0.500 0.1234 0.01553 0.00825 -0.0255 0.9540 1.0000
0.750 0.1769 0.01563 0.00833 -0.0308 0.9429 1.0000
1.000 0.2264 0.01560 0.00830 -0.0351 0.9299 1.0000
1.250 0.2767 0.01548 0.00821 -0.0394 0.9169 1.0000
1.500 0.3295 0.01526 0.00805 -0.0440 0.9041 1.0000
1.750 0.3809 0.01493 0.00779 -0.0480 0.8904 1.0000
2.000 0.4293 0.01454 0.00747 -0.0513 0.8752 1.0000
2.250 0.4669 0.01424 0.00726 -0.0525 0.8557 1.0000
2.500 0.5025 0.01396 0.00702 -0.0531 0.8348 1.0000
2.750 0.5310 0.01379 0.00688 -0.0524 0.8107 1.0000
3.000 0.5578 0.01368 0.00677 -0.0514 0.7855 1.0000
3.250 0.5822 0.01365 0.00676 -0.0500 0.7585 1.0000
3.500 0.6049 0.01370 0.00678 -0.0483 0.7296 1.0000
3.750 0.6270 0.01380 0.00684 -0.0465 0.6993 1.0000
4.000 0.6493 0.01395 0.00693 -0.0448 0.6678 1.0000
4.250 0.6712 0.01415 0.00705 -0.0431 0.6351 1.0000
4.500 0.6921 0.01440 0.00729 -0.0413 0.5997 1.0000
4.750 0.7132 0.01469 0.00750 -0.0396 0.5632 1.0000
5.000 0.7339 0.01504 0.00773 -0.0378 0.5252 1.0000
5.250 0.7538 0.01543 0.00803 -0.0360 0.4842 1.0000
5.500 0.7733 0.01589 0.00838 -0.0342 0.4418 1.0000
5.750 0.7920 0.01642 0.00880 -0.0324 0.3956 1.0000
6.000 0.8099 0.01706 0.00933 -0.0306 0.3471 1.0000
6.250 0.8270 0.01784 0.00992 -0.0287 0.2958 1.0000
6.500 0.8429 0.01882 0.01064 -0.0268 0.2436 1.0000
6.750 0.8582 0.02001 0.01156 -0.0249 0.1944 1.0000
7.000 0.8735 0.02139 0.01269 -0.0231 0.1530 1.0000
7.250 0.8894 0.02294 0.01408 -0.0213 0.1197 1.0000
7.500 0.9061 0.02466 0.01563 -0.0198 0.0964 1.0000
7.750 0.9256 0.02654 0.01760 -0.0183 0.0800 1.0000
8.000 0.9476 0.02888 0.01994 -0.0174 0.0694 1.0000
8.250 0.9679 0.03123 0.02223 -0.0166 0.0597 1.0000
8.500 0.9892 0.03365 0.02513 -0.0151 0.0550 1.0000
8.750 1.0077 0.03595 0.02755 -0.0140 0.0499 1.0000
9.000 1.0207 0.03918 0.03117 -0.0123 0.0460 1.0000
9.250 1.0311 0.04247 0.03500 -0.0100 0.0445 1.0000
9.500 1.0363 0.04625 0.03929 -0.0076 0.0438 1.0000
9.750 1.0364 0.05028 0.04379 -0.0050 0.0438 1.0000
10.000 1.0309 0.05444 0.04838 -0.0024 0.0442 1.0000
10.250 1.0199 0.05864 0.05293 0.0002 0.0446 1.0000
10.500 1.0048 0.06244 0.05699 0.0028 0.0452 1.0000
10.750 0.9866 0.06627 0.06102 0.0048 0.0457 1.0000
11.000 0.9664 0.07061 0.06554 0.0055 0.0461 1.0000
11.250 0.9467 0.07538 0.07045 0.0047 0.0466 1.0000
11.500 0.9266 0.08096 0.07614 0.0025 0.0470 1.0000
11.750 0.9120 0.08732 0.08256 0.0000 0.0477 1.0000
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Polar data table (+)
Polar graphs
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