RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 26 AIRFOIL (raf26-il) Reynolds number: 500,000 Max Cl/Cd: 88.76 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf26-il-500000.txt Download as CSV file: xf-raf26-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 26 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4104 0.08428 0.08210 -0.0218 1.0000 0.0169
-8.750 -0.4132 0.07987 0.07772 -0.0232 1.0000 0.0181
-8.500 -0.4156 0.07568 0.07354 -0.0244 1.0000 0.0184
-8.250 -0.4163 0.07194 0.06983 -0.0262 1.0000 0.0192
-8.000 -0.4205 0.06789 0.06580 -0.0272 1.0000 0.0193
-7.750 -0.4275 0.06389 0.06184 -0.0282 1.0000 0.0194
-7.500 -0.4392 0.06021 0.05820 -0.0288 1.0000 0.0194
-7.250 -0.4460 0.05537 0.05338 -0.0321 1.0000 0.0194
-7.000 -0.4491 0.04955 0.04751 -0.0361 1.0000 0.0194
-6.750 -0.4501 0.04390 0.04176 -0.0385 1.0000 0.0195
-6.500 -0.4496 0.03884 0.03656 -0.0395 1.0000 0.0195
-4.750 -0.3886 0.01735 0.01220 -0.0383 0.9956 0.0149
-4.500 -0.3571 0.01529 0.00979 -0.0390 0.9938 0.0155
-4.250 -0.3257 0.01397 0.00827 -0.0396 0.9912 0.0166
-4.000 -0.2931 0.01293 0.00705 -0.0406 0.9885 0.0178
-3.750 -0.2564 0.01278 0.00682 -0.0424 0.9858 0.0196
-3.500 -0.2246 0.01086 0.00473 -0.0433 0.9838 0.0226
-3.250 -0.1937 0.01029 0.00411 -0.0439 0.9790 0.0260
-3.000 -0.1601 0.00973 0.00348 -0.0451 0.9750 0.0330
-2.750 -0.1248 0.00918 0.00293 -0.0467 0.9722 0.0498
-2.500 -0.0949 0.00866 0.00261 -0.0473 0.9668 0.0992
-2.250 -0.0640 0.00806 0.00238 -0.0482 0.9621 0.1972
-2.000 -0.0311 0.00738 0.00222 -0.0497 0.9589 0.3482
-1.750 -0.0032 0.00696 0.00206 -0.0498 0.9514 0.4422
-1.500 0.0303 0.00647 0.00187 -0.0510 0.9462 0.5329
-1.250 0.0591 0.00598 0.00174 -0.0511 0.9376 0.6443
-1.000 0.0922 0.00528 0.00164 -0.0519 0.9315 0.8161
-0.750 0.1770 0.00519 0.00183 -0.0646 0.9365 1.0000
-0.500 0.2256 0.00508 0.00165 -0.0692 0.9281 1.0000
-0.250 0.2776 0.00497 0.00147 -0.0745 0.9164 1.0000
0.000 0.3264 0.00493 0.00131 -0.0791 0.8951 1.0000
0.250 0.3593 0.00499 0.00126 -0.0801 0.8731 1.0000
0.500 0.3860 0.00508 0.00126 -0.0797 0.8520 1.0000
0.750 0.4106 0.00516 0.00127 -0.0788 0.8309 1.0000
1.000 0.4346 0.00525 0.00128 -0.0778 0.8081 1.0000
1.250 0.4577 0.00535 0.00130 -0.0765 0.7815 1.0000
1.500 0.4802 0.00549 0.00132 -0.0752 0.7507 1.0000
1.750 0.5021 0.00566 0.00138 -0.0737 0.7155 1.0000
2.000 0.5228 0.00589 0.00144 -0.0720 0.6719 1.0000
2.250 0.5428 0.00619 0.00153 -0.0702 0.6199 1.0000
2.500 0.5615 0.00658 0.00164 -0.0681 0.5454 1.0000
2.750 0.5757 0.00735 0.00186 -0.0654 0.4212 1.0000
3.000 0.5933 0.00804 0.00212 -0.0634 0.3131 1.0000
3.250 0.6068 0.00920 0.00256 -0.0609 0.1491 1.0000
3.500 0.6270 0.00980 0.00287 -0.0595 0.0932 1.0000
3.750 0.6498 0.01015 0.00320 -0.0585 0.0838 1.0000
4.000 0.6734 0.01043 0.00352 -0.0576 0.0755 1.0000
4.250 0.6968 0.01073 0.00382 -0.0567 0.0651 1.0000
4.500 0.7195 0.01113 0.00406 -0.0556 0.0318 1.0000
4.750 0.7401 0.01181 0.00475 -0.0540 0.0222 1.0000
5.000 0.7619 0.01235 0.00536 -0.0527 0.0195 1.0000
5.250 0.7831 0.01297 0.00607 -0.0512 0.0176 1.0000
5.500 0.8034 0.01371 0.00687 -0.0497 0.0160 1.0000
5.750 0.8213 0.01486 0.00812 -0.0476 0.0147 1.0000
6.000 0.8364 0.01716 0.01064 -0.0450 0.0138 1.0000
6.250 0.8586 0.01812 0.01173 -0.0438 0.0132 1.0000
6.500 0.8812 0.01901 0.01275 -0.0427 0.0124 1.0000
6.750 0.9024 0.02064 0.01458 -0.0413 0.0120 1.0000
7.000 0.9226 0.02266 0.01686 -0.0396 0.0114 1.0000
7.250 0.9397 0.02564 0.02022 -0.0374 0.0114 1.0000
7.500 0.9495 0.03033 0.02546 -0.0340 0.0121 1.0000
7.750 0.9228 0.04616 0.04227 -0.0264 0.0213 1.0000
8.000 0.9000 0.03561 0.03228 -0.0203 0.0198 1.0000
8.250 0.9021 0.03949 0.03643 -0.0175 0.0187 1.0000
8.500 0.8978 0.04383 0.04099 -0.0148 0.0181 1.0000
8.750 0.8884 0.04822 0.04557 -0.0120 0.0176 1.0000
9.000 0.8729 0.05216 0.04966 -0.0088 0.0174 1.0000
9.250 0.8503 0.05578 0.05341 -0.0055 0.0174 1.0000
9.500 0.8243 0.06013 0.05787 -0.0043 0.0176 1.0000
9.750 0.7958 0.06575 0.06360 -0.0056 0.0180 1.0000
10.000 0.7668 0.07314 0.07107 -0.0096 0.0187 1.0000
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Polar data table (+)
Polar graphs
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