RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 26 AIRFOIL (raf26-il) Reynolds number: 50,000 Max Cl/Cd: 37.08 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf26-il-50000-n5.txt Download as CSV file: xf-raf26-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4918 0.11608 0.10886 -0.0148 1.0000 0.0961
-9.250 -0.4911 0.11283 0.10568 -0.0162 1.0000 0.0980
-9.000 -0.5051 0.11143 0.10444 -0.0204 1.0000 0.1013
-8.500 -0.4849 0.10004 0.09304 -0.0210 1.0000 0.0660
-8.250 -0.4848 0.09530 0.08835 -0.0229 1.0000 0.0519
-8.000 -0.4943 0.09099 0.08417 -0.0274 1.0000 0.0462
-7.750 -0.4909 0.08736 0.08059 -0.0269 1.0000 0.0447
-7.500 -0.4892 0.08339 0.07668 -0.0284 1.0000 0.0432
-7.250 -0.4878 0.07898 0.07234 -0.0309 1.0000 0.0420
-7.000 -0.4851 0.07422 0.06760 -0.0339 1.0000 0.0405
-6.750 -0.4813 0.06878 0.06214 -0.0375 1.0000 0.0390
-6.500 -0.4756 0.06173 0.05474 -0.0430 1.0000 0.0364
-6.250 -0.4670 0.05755 0.05045 -0.0435 1.0000 0.0361
-6.000 -0.4568 0.05327 0.04597 -0.0442 1.0000 0.0358
-5.750 -0.4447 0.04895 0.04136 -0.0448 1.0000 0.0356
-5.500 -0.4302 0.04469 0.03664 -0.0451 1.0000 0.0360
-5.250 -0.4147 0.04087 0.03243 -0.0450 1.0000 0.0374
-5.000 -0.3978 0.03830 0.02968 -0.0445 1.0000 0.0401
-4.750 -0.3783 0.03509 0.02598 -0.0438 1.0000 0.0414
-4.500 -0.3571 0.03205 0.02238 -0.0429 1.0000 0.0425
-4.250 -0.3345 0.02940 0.01917 -0.0418 1.0000 0.0447
-4.000 -0.3124 0.02728 0.01670 -0.0409 1.0000 0.0500
-3.750 -0.2895 0.02552 0.01459 -0.0397 1.0000 0.0562
-3.500 -0.2664 0.02378 0.01258 -0.0383 1.0000 0.0630
-3.250 -0.2430 0.02250 0.01119 -0.0375 1.0000 0.0806
-3.000 -0.2192 0.02118 0.00973 -0.0365 1.0000 0.1050
-2.750 -0.1947 0.01984 0.00848 -0.0361 1.0000 0.1508
-2.500 -0.1707 0.01834 0.00767 -0.0359 1.0000 0.2842
-2.250 -0.1518 0.01713 0.00739 -0.0342 1.0000 0.5124
-1.750 -0.0848 0.01565 0.00650 -0.0349 1.0000 1.0000
-1.500 -0.0633 0.01573 0.00616 -0.0341 1.0000 1.0000
-1.250 -0.0420 0.01585 0.00594 -0.0332 1.0000 1.0000
-1.000 -0.0208 0.01599 0.00579 -0.0323 1.0000 1.0000
-0.750 0.0002 0.01615 0.00568 -0.0315 1.0000 1.0000
-0.500 0.0210 0.01634 0.00567 -0.0307 1.0000 1.0000
-0.250 0.0416 0.01656 0.00570 -0.0298 1.0000 1.0000
0.000 0.0621 0.01681 0.00580 -0.0290 1.0000 1.0000
0.250 0.0823 0.01709 0.00593 -0.0282 1.0000 1.0000
0.500 0.1024 0.01740 0.00613 -0.0275 1.0000 1.0000
0.750 0.1333 0.01780 0.00645 -0.0289 0.9947 1.0000
1.000 0.1746 0.01821 0.00682 -0.0324 0.9834 1.0000
1.250 0.2168 0.01856 0.00716 -0.0359 0.9707 1.0000
1.500 0.2592 0.01884 0.00747 -0.0392 0.9570 1.0000
1.750 0.2982 0.01908 0.00780 -0.0419 0.9440 1.0000
2.000 0.3343 0.01934 0.00814 -0.0439 0.9322 1.0000
2.250 0.3706 0.01960 0.00853 -0.0459 0.9207 1.0000
2.500 0.4080 0.01983 0.00898 -0.0480 0.9095 1.0000
2.750 0.4479 0.02000 0.00937 -0.0504 0.8975 1.0000
3.000 0.4900 0.01997 0.00961 -0.0528 0.8800 1.0000
3.250 0.5387 0.01967 0.00970 -0.0556 0.8570 1.0000
3.500 0.5782 0.01941 0.00977 -0.0565 0.8300 1.0000
3.750 0.6108 0.01915 0.00981 -0.0559 0.7944 1.0000
4.000 0.6439 0.01863 0.00954 -0.0543 0.7333 1.0000
4.250 0.6716 0.01849 0.00948 -0.0521 0.6571 1.0000
4.500 0.6948 0.01874 0.00969 -0.0496 0.5555 1.0000
4.750 0.7069 0.02015 0.01002 -0.0454 0.3447 1.0000
5.000 0.7151 0.02270 0.01144 -0.0426 0.1828 1.0000
5.250 0.7313 0.02467 0.01301 -0.0411 0.1166 1.0000
5.500 0.7474 0.02695 0.01501 -0.0395 0.0781 1.0000
5.750 0.7688 0.02916 0.01737 -0.0380 0.0595 1.0000
6.000 0.7936 0.03109 0.01950 -0.0369 0.0479 1.0000
6.250 0.8196 0.03346 0.02198 -0.0362 0.0423 1.0000
6.500 0.8469 0.03610 0.02503 -0.0352 0.0380 1.0000
6.750 0.8673 0.03839 0.02751 -0.0344 0.0342 1.0000
7.000 0.8889 0.04180 0.03158 -0.0327 0.0324 1.0000
7.250 0.9057 0.04549 0.03584 -0.0309 0.0317 1.0000
7.500 0.9180 0.04932 0.04020 -0.0288 0.0313 1.0000
7.750 0.9261 0.05332 0.04470 -0.0265 0.0311 1.0000
8.000 0.9302 0.05736 0.04920 -0.0243 0.0307 1.0000
8.250 0.9310 0.06136 0.05359 -0.0223 0.0304 1.0000
8.500 0.9275 0.06549 0.05807 -0.0204 0.0302 1.0000
8.750 0.9203 0.06962 0.06248 -0.0187 0.0300 1.0000
9.000 0.9095 0.07375 0.06683 -0.0173 0.0301 1.0000
9.250 0.8943 0.07773 0.07095 -0.0159 0.0303 1.0000
9.500 0.8786 0.08200 0.07532 -0.0158 0.0308 1.0000
9.750 0.8623 0.08698 0.08037 -0.0175 0.0311 1.0000
10.000 0.8486 0.09258 0.08600 -0.0204 0.0317 1.0000
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Polar data table (+)
Polar graphs
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