RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 104 AIRFOIL (rae104-il) Reynolds number: 500,000 Max Cl/Cd: 52.11 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae104-il-500000.txt Download as CSV file: xf-rae104-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 104 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 -0.8168 0.04008 0.03643 -0.0243 1.0000 0.0144
-8.750 -0.8255 0.03570 0.03168 -0.0198 1.0000 0.0140
-8.500 -0.8283 0.03172 0.02730 -0.0155 1.0000 0.0137
-8.250 -0.8251 0.02836 0.02355 -0.0118 1.0000 0.0136
-8.000 -0.8172 0.02563 0.02048 -0.0085 1.0000 0.0137
-7.750 -0.8041 0.02429 0.01894 -0.0060 1.0000 0.0143
-7.500 -0.7910 0.02291 0.01737 -0.0034 1.0000 0.0149
-7.250 -0.7787 0.02136 0.01561 -0.0006 1.0000 0.0152
-7.000 -0.7668 0.02023 0.01431 0.0023 1.0000 0.0155
-6.750 -0.7389 0.01911 0.01302 0.0020 0.9982 0.0159
-6.500 -0.7113 0.01619 0.00988 0.0013 0.9955 0.0173
-6.250 -0.6788 0.01529 0.00894 -0.0001 0.9920 0.0187
-6.000 -0.6456 0.01461 0.00821 -0.0017 0.9880 0.0206
-5.750 -0.6102 0.01414 0.00768 -0.0036 0.9849 0.0226
-5.500 -0.5816 0.01280 0.00626 -0.0043 0.9799 0.0256
-5.250 -0.5490 0.01222 0.00564 -0.0056 0.9752 0.0292
-5.000 -0.5146 0.01159 0.00495 -0.0073 0.9720 0.0352
-4.750 -0.4801 0.01112 0.00447 -0.0091 0.9683 0.0432
-4.500 -0.4506 0.01046 0.00391 -0.0097 0.9610 0.0642
-4.250 -0.4188 0.00974 0.00344 -0.0111 0.9562 0.1224
-4.000 -0.3953 0.00895 0.00307 -0.0108 0.9464 0.2204
-3.750 -0.3739 0.00799 0.00269 -0.0102 0.9376 0.3628
-3.500 -0.3574 0.00702 0.00235 -0.0083 0.9279 0.5227
-3.250 -0.3409 0.00654 0.00231 -0.0058 0.9177 0.6477
-3.000 -0.3158 0.00646 0.00228 -0.0051 0.9108 0.6897
-2.750 -0.2908 0.00644 0.00226 -0.0044 0.9031 0.7157
-2.500 -0.2646 0.00643 0.00224 -0.0039 0.8968 0.7350
-2.250 -0.2390 0.00643 0.00222 -0.0033 0.8897 0.7509
-1.750 -0.1866 0.00647 0.00222 -0.0023 0.8779 0.7780
-1.500 -0.1602 0.00649 0.00222 -0.0019 0.8724 0.7895
-1.250 -0.1340 0.00652 0.00222 -0.0015 0.8669 0.8002
-1.000 -0.1074 0.00653 0.00224 -0.0011 0.8612 0.8095
-0.750 -0.0802 0.00655 0.00224 -0.0009 0.8565 0.8176
-0.500 -0.0540 0.00656 0.00226 -0.0005 0.8505 0.8259
-0.250 -0.0268 0.00656 0.00225 -0.0003 0.8449 0.8324
0.000 0.0000 0.00658 0.00226 0.0000 0.8392 0.8392
0.250 0.0268 0.00656 0.00225 0.0003 0.8324 0.8449
0.500 0.0540 0.00656 0.00226 0.0005 0.8259 0.8505
0.750 0.0802 0.00655 0.00224 0.0009 0.8176 0.8564
1.000 0.1074 0.00653 0.00224 0.0011 0.8095 0.8612
1.250 0.1340 0.00652 0.00222 0.0015 0.8003 0.8669
1.500 0.1602 0.00649 0.00222 0.0019 0.7894 0.8724
1.750 0.1866 0.00647 0.00222 0.0023 0.7779 0.8779
2.250 0.2390 0.00643 0.00221 0.0033 0.7507 0.8897
2.500 0.2646 0.00643 0.00224 0.0039 0.7351 0.8968
2.750 0.2908 0.00644 0.00226 0.0044 0.7158 0.9031
3.000 0.3158 0.00646 0.00228 0.0051 0.6897 0.9108
3.250 0.3408 0.00654 0.00231 0.0059 0.6465 0.9177
3.500 0.3574 0.00701 0.00235 0.0083 0.5229 0.9279
3.750 0.3740 0.00798 0.00269 0.0101 0.3643 0.9375
4.000 0.3952 0.00895 0.00307 0.0108 0.2194 0.9464
4.250 0.4188 0.00974 0.00345 0.0111 0.1222 0.9562
4.500 0.4506 0.01047 0.00391 0.0097 0.0639 0.9611
4.750 0.4800 0.01113 0.00448 0.0091 0.0432 0.9683
5.000 0.5147 0.01158 0.00495 0.0073 0.0356 0.9719
5.250 0.5490 0.01223 0.00564 0.0056 0.0295 0.9752
5.500 0.5817 0.01279 0.00625 0.0043 0.0257 0.9799
5.750 0.6105 0.01408 0.00762 0.0035 0.0225 0.9849
6.000 0.6459 0.01455 0.00814 0.0016 0.0205 0.9880
6.250 0.6789 0.01528 0.00893 0.0001 0.0187 0.9919
6.500 0.7113 0.01619 0.00988 -0.0013 0.0173 0.9955
6.750 0.7390 0.01909 0.01300 -0.0020 0.0159 0.9982
7.000 0.7669 0.02022 0.01430 -0.0023 0.0155 1.0000
7.250 0.7789 0.02132 0.01556 0.0006 0.0151 1.0000
7.500 0.7911 0.02292 0.01737 0.0034 0.0149 1.0000
7.750 0.8037 0.02446 0.01913 0.0061 0.0144 1.0000
8.000 0.8168 0.02578 0.02065 0.0086 0.0138 1.0000
8.250 0.8247 0.02846 0.02367 0.0118 0.0137 1.0000
8.500 0.8284 0.03171 0.02728 0.0155 0.0138 1.0000
8.750 0.8241 0.03595 0.03194 0.0200 0.0142 1.0000
9.000 0.8156 0.04023 0.03658 0.0244 0.0147 1.0000
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Polar data table (+)
Polar graphs
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