RAF 25 AIRFOIL (raf25-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 25 AIRFOIL (raf25-il) Reynolds number: 50,000 Max Cl/Cd: 28.3 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf25-il-50000.txt Download as CSV file: xf-raf25-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 25 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5492 0.09987 0.09291 0.0074 1.0000 0.2792
-8.000 -0.5489 0.09702 0.09011 0.0077 1.0000 0.2964
-7.750 -0.5539 0.09461 0.08780 0.0078 1.0000 0.3123
-7.500 -0.5384 0.09018 0.08338 0.0094 1.0000 0.3321
-7.250 -0.5353 0.08713 0.08038 0.0104 1.0000 0.3516
-7.000 -0.5440 0.08489 0.07827 0.0114 1.0000 0.3700
-6.750 -0.5251 0.08071 0.07406 0.0132 1.0000 0.3928
-6.500 -0.5193 0.07744 0.07085 0.0149 1.0000 0.4156
-6.250 -0.5152 0.07449 0.06796 0.0171 1.0000 0.4420
-6.000 -0.5022 0.07132 0.06475 0.0198 1.0000 0.4764
-5.500 -0.5114 0.04569 0.03763 -0.0300 1.0000 0.1425
-5.250 -0.4916 0.04079 0.03203 -0.0302 1.0000 0.1296
-5.000 -0.4710 0.03677 0.02743 -0.0296 1.0000 0.1242
-4.750 -0.4497 0.03387 0.02406 -0.0287 1.0000 0.1284
-4.500 -0.4264 0.03109 0.02067 -0.0276 1.0000 0.1311
-4.250 -0.4013 0.02853 0.01751 -0.0264 1.0000 0.1329
-4.000 -0.3774 0.02625 0.01512 -0.0254 1.0000 0.1428
-3.750 -0.3525 0.02434 0.01303 -0.0244 1.0000 0.1559
-3.500 -0.3260 0.02247 0.01106 -0.0232 1.0000 0.1690
-3.250 -0.2995 0.02083 0.00948 -0.0224 1.0000 0.1990
-3.000 -0.2754 0.01890 0.00802 -0.0212 1.0000 0.2665
-2.750 -0.1714 0.01545 0.00684 -0.0289 1.0000 1.0000
-2.500 -0.1598 0.01512 0.00618 -0.0270 1.0000 1.0000
-2.250 -0.1446 0.01493 0.00566 -0.0254 1.0000 1.0000
-2.000 -0.1279 0.01481 0.00526 -0.0238 1.0000 1.0000
-1.750 -0.1100 0.01474 0.00493 -0.0223 1.0000 1.0000
-1.500 -0.0915 0.01470 0.00462 -0.0209 1.0000 1.0000
-1.250 -0.0724 0.01470 0.00442 -0.0196 1.0000 1.0000
-1.000 -0.0531 0.01472 0.00427 -0.0183 1.0000 1.0000
-0.750 -0.0337 0.01477 0.00418 -0.0170 1.0000 1.0000
-0.500 -0.0141 0.01484 0.00413 -0.0158 1.0000 1.0000
-0.250 0.0055 0.01495 0.00411 -0.0146 1.0000 1.0000
0.000 0.0249 0.01507 0.00416 -0.0135 1.0000 1.0000
0.250 0.0444 0.01523 0.00425 -0.0124 1.0000 1.0000
0.500 0.0637 0.01542 0.00440 -0.0113 1.0000 1.0000
0.750 0.0828 0.01563 0.00459 -0.0102 1.0000 1.0000
1.000 0.1018 0.01588 0.00484 -0.0092 1.0000 1.0000
1.250 0.1206 0.01617 0.00514 -0.0082 1.0000 1.0000
1.500 0.1392 0.01649 0.00549 -0.0073 1.0000 1.0000
1.750 0.1575 0.01686 0.00591 -0.0065 1.0000 1.0000
2.000 0.1755 0.01728 0.00639 -0.0057 1.0000 1.0000
2.250 0.1931 0.01775 0.00698 -0.0050 1.0000 1.0000
2.500 0.2104 0.01828 0.00761 -0.0044 1.0000 1.0000
2.750 0.2270 0.01889 0.00833 -0.0039 1.0000 1.0000
3.000 0.2432 0.01957 0.00914 -0.0035 1.0000 1.0000
3.250 0.2588 0.02034 0.01006 -0.0032 1.0000 1.0000
3.500 0.2737 0.02122 0.01111 -0.0031 1.0000 1.0000
3.750 0.3772 0.02285 0.01356 -0.0191 0.9556 1.0000
4.000 0.5372 0.01898 0.00875 -0.0206 0.3109 1.0000
4.250 0.5521 0.02207 0.01056 -0.0184 0.1942 1.0000
4.500 0.5772 0.02409 0.01239 -0.0173 0.1568 1.0000
4.750 0.6077 0.02641 0.01460 -0.0166 0.1380 1.0000
5.000 0.6366 0.02870 0.01705 -0.0159 0.1233 1.0000
5.250 0.6658 0.03125 0.01997 -0.0149 0.1183 1.0000
5.500 0.6919 0.03450 0.02326 -0.0143 0.1122 1.0000
5.750 0.7147 0.03702 0.02649 -0.0126 0.1086 1.0000
6.000 0.7370 0.04054 0.03050 -0.0113 0.1100 1.0000
6.250 0.7578 0.04424 0.03473 -0.0099 0.1138 1.0000
6.500 0.7734 0.04876 0.04006 -0.0084 0.1232 1.0000
6.750 0.7873 0.05387 0.04584 -0.0075 0.1370 1.0000
7.000 0.7953 0.06044 0.05317 -0.0081 0.1640 1.0000
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Polar data table (+)
Polar graphs
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