RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Reynolds number: 50,000 Max Cl/Cd: 34.13 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14a147-il-50000-n5.txt Download as CSV file: xf-rg14a147-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14A-1.4/7.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5234 0.09122 0.08444 -0.0165 1.0000 0.0474
-8.000 -0.5234 0.08723 0.08052 -0.0181 1.0000 0.0455
-7.750 -0.5256 0.08281 0.07618 -0.0208 1.0000 0.0437
-7.500 -0.5264 0.07784 0.07123 -0.0242 1.0000 0.0418
-7.000 -0.5234 0.06713 0.06023 -0.0311 1.0000 0.0372
-6.750 -0.5172 0.06307 0.05611 -0.0314 1.0000 0.0365
-6.500 -0.5101 0.05892 0.05182 -0.0319 1.0000 0.0360
-6.250 -0.5013 0.05478 0.04748 -0.0322 1.0000 0.0355
-6.000 -0.4906 0.05067 0.04297 -0.0323 1.0000 0.0350
-5.750 -0.4778 0.04666 0.03861 -0.0321 1.0000 0.0347
-5.500 -0.4628 0.04287 0.03442 -0.0315 1.0000 0.0345
-5.250 -0.4456 0.03929 0.03037 -0.0308 1.0000 0.0345
-5.000 -0.4264 0.03597 0.02654 -0.0298 1.0000 0.0348
-4.750 -0.4050 0.03297 0.02298 -0.0287 1.0000 0.0360
-4.500 -0.3834 0.03045 0.02001 -0.0277 1.0000 0.0394
-4.250 -0.3616 0.02856 0.01792 -0.0269 1.0000 0.0447
-4.000 -0.3371 0.02642 0.01538 -0.0255 1.0000 0.0476
-3.750 -0.3127 0.02449 0.01314 -0.0240 1.0000 0.0511
-3.500 -0.2898 0.02290 0.01146 -0.0227 1.0000 0.0573
-3.250 -0.2662 0.02166 0.01007 -0.0216 1.0000 0.0751
-3.000 -0.2433 0.02018 0.00865 -0.0206 1.0000 0.1039
-2.750 -0.2238 0.01805 0.00757 -0.0198 1.0000 0.2530
-2.500 -0.2161 0.01583 0.00720 -0.0152 1.0000 0.6327
-2.250 -0.1171 0.01544 0.00659 -0.0251 1.0000 1.0000
-2.000 -0.1029 0.01532 0.00617 -0.0230 1.0000 1.0000
-1.750 -0.0882 0.01524 0.00582 -0.0210 1.0000 1.0000
-1.500 -0.0726 0.01519 0.00553 -0.0191 1.0000 1.0000
-1.250 -0.0562 0.01518 0.00530 -0.0174 1.0000 1.0000
-1.000 -0.0390 0.01521 0.00505 -0.0158 1.0000 1.0000
-0.750 -0.0212 0.01526 0.00494 -0.0144 1.0000 1.0000
-0.500 -0.0030 0.01535 0.00487 -0.0131 1.0000 1.0000
-0.250 0.0154 0.01547 0.00486 -0.0119 1.0000 1.0000
0.000 0.0340 0.01563 0.00490 -0.0107 1.0000 1.0000
0.250 0.0527 0.01582 0.00496 -0.0097 1.0000 1.0000
0.500 0.0712 0.01605 0.00512 -0.0087 1.0000 1.0000
0.750 0.1044 0.01638 0.00540 -0.0107 0.9920 1.0000
1.000 0.1497 0.01672 0.00573 -0.0149 0.9761 1.0000
1.250 0.1942 0.01700 0.00605 -0.0188 0.9594 1.0000
1.500 0.2396 0.01723 0.00632 -0.0226 0.9427 1.0000
1.750 0.2817 0.01737 0.00656 -0.0256 0.9237 1.0000
2.000 0.3266 0.01746 0.00677 -0.0289 0.9049 1.0000
2.250 0.3680 0.01749 0.00700 -0.0313 0.8837 1.0000
2.500 0.4090 0.01748 0.00715 -0.0333 0.8611 1.0000
2.750 0.4455 0.01747 0.00730 -0.0343 0.8347 1.0000
3.000 0.4782 0.01749 0.00755 -0.0345 0.8046 1.0000
3.250 0.5097 0.01751 0.00771 -0.0342 0.7716 1.0000
3.500 0.5396 0.01758 0.00788 -0.0335 0.7360 1.0000
3.750 0.5651 0.01776 0.00816 -0.0321 0.6947 1.0000
4.000 0.5897 0.01796 0.00840 -0.0304 0.6500 1.0000
4.250 0.6126 0.01825 0.00881 -0.0285 0.6006 1.0000
4.500 0.6340 0.01864 0.00916 -0.0265 0.5457 1.0000
4.750 0.6543 0.01917 0.00959 -0.0244 0.4851 1.0000
5.000 0.6735 0.01985 0.01012 -0.0225 0.4162 1.0000
5.250 0.6912 0.02075 0.01076 -0.0206 0.3372 1.0000
5.500 0.7079 0.02197 0.01162 -0.0189 0.2482 1.0000
5.750 0.7243 0.02367 0.01281 -0.0177 0.1635 1.0000
6.000 0.7418 0.02559 0.01434 -0.0166 0.1063 1.0000
6.250 0.7602 0.02752 0.01618 -0.0153 0.0818 1.0000
6.500 0.7799 0.02948 0.01823 -0.0139 0.0694 1.0000
6.750 0.7996 0.03127 0.02027 -0.0128 0.0575 1.0000
7.000 0.8220 0.03327 0.02264 -0.0116 0.0501 1.0000
7.250 0.8431 0.03584 0.02531 -0.0106 0.0464 1.0000
7.500 0.8654 0.03898 0.02894 -0.0094 0.0441 1.0000
7.750 0.8838 0.04254 0.03310 -0.0080 0.0423 1.0000
8.000 0.8972 0.04645 0.03760 -0.0065 0.0408 1.0000
8.250 0.9074 0.04961 0.04113 -0.0052 0.0375 1.0000
8.500 0.9145 0.05292 0.04446 -0.0044 0.0342 1.0000
8.750 0.9134 0.05695 0.04917 -0.0028 0.0329 1.0000
9.000 0.9090 0.06130 0.05394 -0.0016 0.0325 1.0000
9.250 0.8999 0.06574 0.05871 -0.0007 0.0324 1.0000
9.500 0.8868 0.06994 0.06313 -0.0001 0.0324 1.0000
9.750 0.8702 0.07427 0.06760 -0.0003 0.0326 1.0000
10.000 0.8535 0.07925 0.07269 -0.0023 0.0328 1.0000
10.250 0.8388 0.08491 0.07841 -0.0058 0.0331 1.0000
10.500 0.8248 0.09161 0.08513 -0.0106 0.0334 1.0000
10.750 0.8148 0.09849 0.09201 -0.0152 0.0337 1.0000
11.000 0.8069 0.10557 0.09906 -0.0195 0.0339 1.0000
11.250 0.8016 0.11226 0.10572 -0.0231 0.0341 1.0000
11.500 0.7983 0.11856 0.11198 -0.0262 0.0343 1.0000
12.000 0.6678 0.12935 0.12315 -0.0267 0.0448 1.0000
12.250 0.6627 0.13428 0.12807 -0.0291 0.0446 1.0000
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Polar data table (+)
Polar graphs
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