RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 27 AIRFOIL (raf27-il) Reynolds number: 100,000 Max Cl/Cd: 39.5 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf27-il-100000.txt Download as CSV file: xf-raf27-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 27 AIRFOIL
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 -0.6443 0.09158 0.08662 -0.0105 1.0000 0.1673
-9.250 -0.7829 0.06509 0.05965 -0.0280 1.0000 0.0811
-9.000 -0.8126 0.05769 0.05160 -0.0252 1.0000 0.0686
-8.750 -0.8123 0.05318 0.04688 -0.0235 1.0000 0.0678
-8.500 -0.8119 0.04915 0.04252 -0.0212 1.0000 0.0675
-8.250 -0.8079 0.04512 0.03816 -0.0190 1.0000 0.0667
-8.000 -0.8016 0.04129 0.03392 -0.0165 1.0000 0.0657
-7.750 -0.7922 0.03786 0.03005 -0.0140 1.0000 0.0652
-7.500 -0.7797 0.03487 0.02660 -0.0116 1.0000 0.0657
-7.250 -0.7652 0.03284 0.02404 -0.0091 1.0000 0.0683
-7.000 -0.7480 0.03003 0.02093 -0.0074 1.0000 0.0711
-6.750 -0.7270 0.02786 0.01862 -0.0061 1.0000 0.0742
-6.500 -0.7056 0.02625 0.01681 -0.0047 1.0000 0.0792
-6.250 -0.6836 0.02440 0.01483 -0.0035 1.0000 0.0852
-6.000 -0.6613 0.02290 0.01332 -0.0023 1.0000 0.0919
-5.750 -0.6406 0.02145 0.01191 -0.0009 1.0000 0.1013
-5.500 -0.6211 0.02011 0.01059 0.0009 1.0000 0.1126
-5.250 -0.6043 0.01887 0.00952 0.0029 1.0000 0.1303
-5.000 -0.5901 0.01745 0.00842 0.0054 1.0000 0.1667
-4.750 -0.5823 0.01561 0.00749 0.0088 1.0000 0.2855
-4.500 -0.5716 0.01460 0.00711 0.0120 1.0000 0.4046
-4.250 -0.5565 0.01409 0.00683 0.0146 1.0000 0.4813
-4.000 -0.5405 0.01368 0.00667 0.0173 1.0000 0.5467
-3.750 -0.5249 0.01342 0.00667 0.0204 1.0000 0.6120
-3.500 -0.5087 0.01328 0.00669 0.0235 1.0000 0.6695
-3.250 -0.4908 0.01316 0.00664 0.0262 1.0000 0.7153
-3.000 -0.4716 0.01309 0.00664 0.0287 1.0000 0.7573
-2.750 -0.4518 0.01314 0.00677 0.0315 1.0000 0.8019
-2.500 -0.4274 0.01332 0.00697 0.0335 1.0000 0.8439
-2.250 -0.3935 0.01357 0.00714 0.0334 1.0000 0.8779
-2.000 -0.3467 0.01392 0.00736 0.0304 1.0000 0.9047
-1.750 -0.2943 0.01426 0.00755 0.0261 1.0000 0.9276
-1.500 -0.2281 0.01459 0.00770 0.0189 1.0000 0.9434
-1.250 -0.1625 0.01476 0.00775 0.0116 1.0000 0.9585
-1.000 -0.0975 0.01477 0.00764 0.0040 1.0000 0.9737
-0.750 -0.0317 0.01461 0.00741 -0.0040 1.0000 0.9885
-0.500 0.0245 0.01432 0.00708 -0.0106 1.0000 1.0000
-0.250 0.0170 0.01415 0.00695 -0.0061 1.0000 1.0000
0.000 0.0000 0.01410 0.00692 0.0000 1.0000 1.0000
0.250 -0.0169 0.01415 0.00695 0.0061 1.0000 1.0000
0.500 -0.0244 0.01432 0.00708 0.0106 1.0000 1.0000
0.750 0.0319 0.01460 0.00741 0.0040 0.9884 1.0000
1.000 0.0975 0.01477 0.00764 -0.0040 0.9737 1.0000
1.250 0.1625 0.01476 0.00774 -0.0116 0.9585 1.0000
1.500 0.2283 0.01458 0.00770 -0.0190 0.9434 1.0000
1.750 0.2943 0.01426 0.00755 -0.0261 0.9277 1.0000
2.000 0.3466 0.01392 0.00736 -0.0304 0.9047 1.0000
2.250 0.3935 0.01358 0.00714 -0.0334 0.8782 1.0000
2.500 0.4275 0.01332 0.00697 -0.0335 0.8439 1.0000
2.750 0.4518 0.01314 0.00676 -0.0315 0.8017 1.0000
3.000 0.4717 0.01309 0.00664 -0.0287 0.7572 1.0000
3.250 0.4909 0.01316 0.00666 -0.0262 0.7154 1.0000
3.500 0.5089 0.01328 0.00670 -0.0235 0.6697 1.0000
3.750 0.5250 0.01342 0.00667 -0.0204 0.6121 1.0000
4.000 0.5405 0.01369 0.00667 -0.0173 0.5463 1.0000
4.250 0.5566 0.01409 0.00683 -0.0147 0.4814 1.0000
4.500 0.5717 0.01460 0.00711 -0.0120 0.4043 1.0000
4.750 0.5824 0.01561 0.00749 -0.0088 0.2857 1.0000
5.000 0.5900 0.01747 0.00843 -0.0054 0.1663 1.0000
5.250 0.6043 0.01886 0.00952 -0.0029 0.1302 1.0000
5.500 0.6211 0.02011 0.01060 -0.0009 0.1125 1.0000
5.750 0.6407 0.02145 0.01192 0.0009 0.1015 1.0000
6.000 0.6614 0.02291 0.01333 0.0022 0.0920 1.0000
6.250 0.6837 0.02440 0.01483 0.0035 0.0852 1.0000
6.500 0.7056 0.02624 0.01681 0.0047 0.0791 1.0000
6.750 0.7270 0.02786 0.01862 0.0061 0.0741 1.0000
7.000 0.7480 0.03004 0.02094 0.0074 0.0711 1.0000
7.250 0.7653 0.03289 0.02409 0.0091 0.0684 1.0000
7.500 0.7797 0.03487 0.02659 0.0116 0.0657 1.0000
7.750 0.7923 0.03786 0.03005 0.0140 0.0652 1.0000
8.000 0.8015 0.04129 0.03393 0.0165 0.0657 1.0000
8.250 0.8078 0.04513 0.03817 0.0190 0.0667 1.0000
8.500 0.8115 0.04913 0.04251 0.0213 0.0674 1.0000
8.750 0.8125 0.05321 0.04690 0.0235 0.0679 1.0000
9.000 0.8141 0.05792 0.05179 0.0250 0.0688 1.0000
9.250 0.8022 0.06649 0.06081 0.0267 0.0822 1.0000
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Polar data table (+)
Polar graphs
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