RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 500,000 Max Cl/Cd: 47.93 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf30md-il-500000.txt Download as CSV file: xf-raf30md-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 30 MOD 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.7723 0.04312 0.03988 -0.0181 1.0000 0.0155
-8.000 -0.7759 0.03739 0.03376 -0.0162 1.0000 0.0148
-7.750 -0.7736 0.03193 0.02780 -0.0138 1.0000 0.0141
-7.500 -0.7645 0.02747 0.02283 -0.0114 1.0000 0.0139
-7.250 -0.7482 0.02487 0.01988 -0.0097 1.0000 0.0145
-7.000 -0.7285 0.02316 0.01787 -0.0084 1.0000 0.0154
-6.750 -0.7080 0.02153 0.01596 -0.0070 1.0000 0.0160
-6.500 -0.6869 0.02007 0.01424 -0.0057 1.0000 0.0165
-6.250 -0.6694 0.01683 0.01075 -0.0040 1.0000 0.0176
-6.000 -0.6474 0.01590 0.00977 -0.0030 1.0000 0.0186
-5.750 -0.6246 0.01526 0.00908 -0.0021 1.0000 0.0201
-5.500 -0.6012 0.01477 0.00851 -0.0012 1.0000 0.0220
-5.250 -0.5775 0.01434 0.00801 -0.0003 1.0000 0.0234
-5.000 -0.5588 0.01276 0.00633 0.0014 1.0000 0.0255
-4.750 -0.5376 0.01198 0.00553 0.0027 1.0000 0.0282
-4.500 -0.5149 0.01155 0.00507 0.0037 1.0000 0.0314
-4.250 -0.4916 0.01122 0.00469 0.0046 1.0000 0.0337
-4.000 -0.4713 0.01041 0.00381 0.0061 1.0000 0.0371
-3.750 -0.4491 0.00996 0.00334 0.0072 1.0000 0.0413
-3.500 -0.4263 0.00966 0.00301 0.0082 1.0000 0.0450
-3.250 -0.4037 0.00932 0.00264 0.0093 1.0000 0.0503
-3.000 -0.3815 0.00898 0.00235 0.0104 1.0000 0.0640
-2.750 -0.3628 0.00811 0.00204 0.0118 1.0000 0.1868
-2.500 -0.3444 0.00731 0.00185 0.0131 1.0000 0.3375
-2.250 -0.3214 0.00673 0.00177 0.0137 0.9991 0.4629
-2.000 -0.2846 0.00625 0.00174 0.0115 0.9943 0.5824
-1.750 -0.2483 0.00598 0.00169 0.0096 0.9882 0.6455
-1.500 -0.2094 0.00579 0.00166 0.0072 0.9832 0.6923
-1.250 -0.1745 0.00559 0.00161 0.0058 0.9755 0.7362
-1.000 -0.1361 0.00540 0.00158 0.0037 0.9700 0.7845
-0.750 -0.1036 0.00519 0.00157 0.0031 0.9598 0.8332
-0.500 -0.0701 0.00505 0.00158 0.0024 0.9492 0.8758
-0.250 -0.0351 0.00499 0.00157 0.0012 0.9365 0.9010
0.000 0.0000 0.00497 0.00157 0.0000 0.9203 0.9203
0.250 0.0351 0.00499 0.00157 -0.0012 0.9012 0.9364
0.500 0.0701 0.00505 0.00158 -0.0023 0.8752 0.9492
0.750 0.1036 0.00520 0.00157 -0.0031 0.8323 0.9598
1.000 0.1361 0.00540 0.00158 -0.0037 0.7838 0.9699
1.250 0.1745 0.00559 0.00161 -0.0058 0.7375 0.9755
1.500 0.2095 0.00579 0.00166 -0.0072 0.6941 0.9832
1.750 0.2483 0.00598 0.00169 -0.0096 0.6457 0.9882
2.000 0.2847 0.00626 0.00174 -0.0115 0.5819 0.9942
2.250 0.3216 0.00671 0.00177 -0.0137 0.4671 0.9990
2.500 0.3447 0.00731 0.00186 -0.0132 0.3379 1.0000
2.750 0.3630 0.00812 0.00205 -0.0118 0.1844 1.0000
3.000 0.3818 0.00899 0.00236 -0.0105 0.0636 1.0000
3.250 0.4041 0.00933 0.00264 -0.0094 0.0501 1.0000
3.500 0.4266 0.00967 0.00301 -0.0083 0.0450 1.0000
3.750 0.4494 0.00997 0.00335 -0.0073 0.0413 1.0000
4.000 0.4716 0.01042 0.00381 -0.0062 0.0371 1.0000
4.250 0.4920 0.01121 0.00468 -0.0047 0.0337 1.0000
4.500 0.5152 0.01154 0.00507 -0.0037 0.0313 1.0000
4.750 0.5378 0.01199 0.00554 -0.0027 0.0281 1.0000
5.000 0.5591 0.01274 0.00631 -0.0015 0.0257 1.0000
5.250 0.5776 0.01437 0.00804 0.0003 0.0234 1.0000
5.500 0.6013 0.01479 0.00854 0.0012 0.0221 1.0000
5.750 0.6247 0.01525 0.00907 0.0021 0.0201 1.0000
6.000 0.6474 0.01595 0.00982 0.0031 0.0187 1.0000
6.250 0.6695 0.01685 0.01077 0.0040 0.0176 1.0000
6.500 0.6864 0.02033 0.01453 0.0058 0.0165 1.0000
6.750 0.7083 0.02140 0.01583 0.0070 0.0160 1.0000
7.000 0.7283 0.02320 0.01791 0.0084 0.0155 1.0000
7.250 0.7487 0.02464 0.01963 0.0097 0.0144 1.0000
7.500 0.7645 0.02746 0.02281 0.0114 0.0139 1.0000
7.750 0.7740 0.03175 0.02761 0.0137 0.0140 1.0000
8.000 0.7758 0.03739 0.03376 0.0162 0.0147 1.0000
8.250 0.7724 0.04306 0.03982 0.0182 0.0155 1.0000
8.500 0.7509 0.05414 0.05154 0.0203 0.0191 1.0000
8.750 0.7437 0.05888 0.05645 0.0205 0.0190 1.0000
9.000 0.7339 0.06289 0.06057 0.0205 0.0186 1.0000
9.250 0.7061 0.06947 0.06724 0.0178 0.0190 1.0000
9.500 0.6836 0.08040 0.07818 0.0070 0.0197 1.0000
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Polar data table (+)
Polar graphs
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