DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DAE-51 AIRFOIL (dae51-il) Reynolds number: 500,000 Max Cl/Cd: 110.34 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae51-il-500000-n5.txt Download as CSV file: xf-dae51-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DAE-51 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3391 0.08699 0.08465 -0.0386 0.9285 0.0105
-8.250 -0.3364 0.08323 0.08087 -0.0405 0.9152 0.0104
-8.000 -0.3333 0.07932 0.07693 -0.0429 0.9033 0.0104
-7.750 -0.3301 0.07519 0.07278 -0.0461 0.8923 0.0105
-7.500 -0.3228 0.07008 0.06762 -0.0518 0.8828 0.0107
-7.250 -0.3100 0.06388 0.06138 -0.0602 0.8737 0.0108
-7.000 -0.2928 0.05683 0.05424 -0.0700 0.8660 0.0107
-6.750 -0.2713 0.04730 0.04453 -0.0819 0.8583 0.0104
-6.500 -0.2560 0.02269 0.01839 -0.0975 0.8517 0.0102
-6.250 -0.2311 0.01866 0.01367 -0.0986 0.8458 0.0107
-6.000 -0.2047 0.01678 0.01138 -0.0989 0.8403 0.0110
-5.750 -0.1776 0.01552 0.00983 -0.0991 0.8350 0.0113
-5.500 -0.1500 0.01459 0.00867 -0.0992 0.8293 0.0115
-5.250 -0.1228 0.01356 0.00743 -0.0994 0.8242 0.0119
-5.000 -0.0951 0.01297 0.00677 -0.0995 0.8187 0.0124
-4.750 -0.0671 0.01257 0.00629 -0.0997 0.8130 0.0130
-4.500 -0.0393 0.01208 0.00570 -0.0997 0.8079 0.0136
-4.250 -0.0110 0.01153 0.00505 -0.0998 0.8021 0.0141
-4.000 0.0172 0.01108 0.00449 -0.0999 0.7964 0.0147
-3.750 0.0455 0.01071 0.00404 -0.1000 0.7911 0.0153
-3.500 0.0739 0.01024 0.00353 -0.1002 0.7851 0.0164
-3.250 0.1022 0.00998 0.00320 -0.1003 0.7795 0.0175
-3.000 0.1309 0.00974 0.00292 -0.1004 0.7735 0.0190
-2.750 0.1594 0.00951 0.00264 -0.1006 0.7673 0.0213
-2.500 0.1880 0.00932 0.00242 -0.1007 0.7614 0.0244
-2.250 0.2166 0.00912 0.00220 -0.1008 0.7547 0.0283
-2.000 0.2452 0.00897 0.00202 -0.1009 0.7485 0.0356
-1.750 0.2738 0.00879 0.00188 -0.1011 0.7414 0.0485
-1.250 0.3310 0.00842 0.00166 -0.1015 0.7273 0.1142
-0.750 0.3878 0.00785 0.00154 -0.1021 0.7120 0.2833
-0.500 0.4161 0.00761 0.00152 -0.1023 0.7042 0.3779
-0.250 0.4443 0.00738 0.00153 -0.1026 0.6954 0.4687
0.000 0.4722 0.00712 0.00156 -0.1027 0.6867 0.5812
0.250 0.4990 0.00686 0.00160 -0.1025 0.6773 0.6969
0.500 0.5240 0.00660 0.00165 -0.1016 0.6675 0.8077
0.750 0.5497 0.00629 0.00158 -0.1007 0.6573 1.0000
1.000 0.5780 0.00639 0.00159 -0.1008 0.6464 1.0000
1.250 0.6063 0.00648 0.00161 -0.1008 0.6345 1.0000
1.500 0.6344 0.00659 0.00164 -0.1009 0.6222 1.0000
1.750 0.6624 0.00670 0.00168 -0.1009 0.6095 1.0000
2.000 0.6903 0.00683 0.00174 -0.1009 0.5962 1.0000
2.250 0.7181 0.00697 0.00181 -0.1009 0.5827 1.0000
2.500 0.7458 0.00712 0.00189 -0.1009 0.5688 1.0000
2.750 0.7734 0.00728 0.00198 -0.1009 0.5545 1.0000
3.000 0.8009 0.00744 0.00209 -0.1009 0.5396 1.0000
3.250 0.8282 0.00762 0.00221 -0.1008 0.5241 1.0000
3.500 0.8554 0.00781 0.00234 -0.1008 0.5078 1.0000
3.750 0.8824 0.00801 0.00248 -0.1007 0.4907 1.0000
4.000 0.9091 0.00824 0.00265 -0.1006 0.4729 1.0000
4.250 0.9357 0.00848 0.00283 -0.1004 0.4536 1.0000
4.500 0.9620 0.00875 0.00302 -0.1002 0.4315 1.0000
4.750 0.9878 0.00906 0.00325 -0.1000 0.4073 1.0000
5.000 1.0131 0.00942 0.00350 -0.0997 0.3792 1.0000
5.250 1.0374 0.00989 0.00380 -0.0993 0.3425 1.0000
5.500 1.0615 0.01037 0.00412 -0.0989 0.3091 1.0000
5.750 1.0856 0.01085 0.00447 -0.0984 0.2779 1.0000
6.000 1.1079 0.01150 0.00490 -0.0978 0.2347 1.0000
6.250 1.1300 0.01218 0.00536 -0.0971 0.1946 1.0000
6.500 1.1527 0.01276 0.00581 -0.0965 0.1647 1.0000
6.750 1.1750 0.01337 0.00629 -0.0959 0.1369 1.0000
7.000 1.1966 0.01402 0.00680 -0.0951 0.1092 1.0000
7.250 1.2178 0.01469 0.00735 -0.0943 0.0859 1.0000
7.500 1.2391 0.01533 0.00789 -0.0935 0.0672 1.0000
7.750 1.2598 0.01599 0.00849 -0.0926 0.0521 1.0000
8.000 1.2806 0.01661 0.00907 -0.0917 0.0413 1.0000
8.250 1.3009 0.01725 0.00968 -0.0907 0.0334 1.0000
8.500 1.3213 0.01784 0.01027 -0.0898 0.0278 1.0000
8.750 1.3412 0.01845 0.01091 -0.0887 0.0240 1.0000
9.000 1.3602 0.01909 0.01158 -0.0876 0.0212 1.0000
9.250 1.3784 0.01977 0.01230 -0.0863 0.0190 1.0000
9.500 1.3964 0.02041 0.01299 -0.0850 0.0175 1.0000
9.750 1.4118 0.02113 0.01375 -0.0834 0.0160 1.0000
10.000 1.4243 0.02197 0.01465 -0.0812 0.0147 1.0000
10.250 1.4383 0.02273 0.01549 -0.0795 0.0139 1.0000
10.500 1.4512 0.02358 0.01642 -0.0776 0.0132 1.0000
10.750 1.4632 0.02452 0.01744 -0.0758 0.0125 1.0000
11.000 1.4737 0.02561 0.01859 -0.0740 0.0118 1.0000
11.250 1.4809 0.02699 0.02004 -0.0719 0.0111 1.0000
11.500 1.4912 0.02816 0.02131 -0.0703 0.0108 1.0000
11.750 1.5010 0.02941 0.02267 -0.0687 0.0103 1.0000
12.000 1.5098 0.03077 0.02413 -0.0672 0.0098 1.0000
12.250 1.5178 0.03224 0.02569 -0.0657 0.0094 1.0000
12.500 1.5248 0.03384 0.02738 -0.0643 0.0090 1.0000
12.750 1.5304 0.03562 0.02924 -0.0629 0.0087 1.0000
13.000 1.5339 0.03765 0.03137 -0.0616 0.0084 1.0000
13.250 1.5339 0.04008 0.03390 -0.0602 0.0082 1.0000
13.500 1.5341 0.04257 0.03651 -0.0591 0.0080 1.0000
13.750 1.5363 0.04494 0.03900 -0.0582 0.0079 1.0000
14.000 1.5368 0.04752 0.04173 -0.0573 0.0077 1.0000
14.250 1.5365 0.05030 0.04464 -0.0567 0.0075 1.0000
14.500 1.5349 0.05329 0.04776 -0.0562 0.0074 1.0000
14.750 1.5325 0.05648 0.05108 -0.0559 0.0072 1.0000
15.000 1.5295 0.05989 0.05462 -0.0558 0.0071 1.0000
15.250 1.5259 0.06350 0.05836 -0.0559 0.0069 1.0000
15.500 1.5219 0.06728 0.06227 -0.0563 0.0068 1.0000
15.750 1.5170 0.07129 0.06641 -0.0568 0.0067 1.0000
16.000 1.5117 0.07549 0.07074 -0.0576 0.0065 1.0000
16.250 1.5055 0.07997 0.07534 -0.0587 0.0064 1.0000
16.500 1.4981 0.08469 0.08018 -0.0599 0.0063 1.0000
16.750 1.4895 0.08972 0.08535 -0.0614 0.0062 1.0000
17.000 1.4803 0.09499 0.09074 -0.0631 0.0062 1.0000
17.250 1.4701 0.10054 0.09642 -0.0650 0.0061 1.0000
17.500 1.4590 0.10633 0.10233 -0.0672 0.0060 1.0000
17.750 1.4467 0.11244 0.10857 -0.0696 0.0060 1.0000
18.000 1.4344 0.11871 0.11497 -0.0723 0.0059 1.0000
18.250 1.4219 0.12516 0.12154 -0.0753 0.0058 1.0000
18.500 1.4091 0.13175 0.12826 -0.0784 0.0058 1.0000
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Polar data table (+)
Polar graphs
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