dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 50,000 Max Cl/Cd: 24.19 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dh4009sm-il-50000-n5.txt Download as CSV file: xf-dh4009sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: dh4009sm
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6085 0.06193 0.05509 -0.0272 1.0000 0.0672
-7.750 -0.6803 0.06985 0.06235 -0.0218 1.0000 0.0599
-7.500 -0.6770 0.06584 0.05811 -0.0209 1.0000 0.0577
-7.250 -0.6731 0.06193 0.05395 -0.0197 1.0000 0.0552
-7.000 -0.6668 0.05956 0.05076 -0.0172 1.0000 0.0493
-6.750 -0.6554 0.05532 0.04643 -0.0162 1.0000 0.0483
-6.500 -0.6440 0.05167 0.04257 -0.0148 1.0000 0.0469
-6.250 -0.6312 0.04831 0.03892 -0.0132 1.0000 0.0451
-6.000 -0.6165 0.04520 0.03544 -0.0115 1.0000 0.0435
-5.750 -0.5999 0.04229 0.03210 -0.0097 1.0000 0.0420
-5.500 -0.5810 0.03958 0.02896 -0.0079 1.0000 0.0407
-5.250 -0.5601 0.03709 0.02603 -0.0063 1.0000 0.0398
-5.000 -0.5374 0.03483 0.02336 -0.0049 1.0000 0.0392
-4.750 -0.5133 0.03274 0.02091 -0.0036 1.0000 0.0389
-4.500 -0.4877 0.03079 0.01863 -0.0027 1.0000 0.0390
-4.250 -0.4606 0.02900 0.01668 -0.0019 1.0000 0.0395
-4.000 -0.4338 0.02749 0.01508 -0.0011 1.0000 0.0418
-3.750 -0.4087 0.02632 0.01377 -0.0001 1.0000 0.0460
-3.500 -0.3858 0.02530 0.01255 0.0014 1.0000 0.0489
-3.250 -0.3665 0.02413 0.01126 0.0031 1.0000 0.0508
-3.000 -0.3488 0.02301 0.00997 0.0048 1.0000 0.0540
-2.750 -0.3298 0.02210 0.00890 0.0063 1.0000 0.0591
-2.500 -0.3111 0.02116 0.00789 0.0077 1.0000 0.0727
-2.250 -0.2973 0.01927 0.00681 0.0094 1.0000 0.1885
-2.000 -0.2099 0.01990 0.00974 0.0101 1.0000 0.9401
-1.750 -0.1753 0.01960 0.00909 0.0080 1.0000 0.9482
-1.500 -0.1436 0.01932 0.00859 0.0064 1.0000 0.9578
-1.250 -0.1068 0.01905 0.00813 0.0037 1.0000 0.9657
-1.000 -0.0724 0.01881 0.00776 0.0014 1.0000 0.9746
-0.750 -0.0381 0.01860 0.00743 -0.0009 1.0000 0.9842
-0.500 -0.0022 0.01839 0.00716 -0.0037 1.0000 0.9933
-0.250 0.0250 0.01822 0.00698 -0.0048 1.0000 1.0000
0.000 0.0285 0.01811 0.00691 -0.0015 1.0000 1.0000
0.250 0.0284 0.01805 0.00689 0.0024 1.0000 1.0000
0.500 0.0262 0.01803 0.00689 0.0066 1.0000 1.0000
0.750 0.0249 0.01806 0.00691 0.0107 1.0000 1.0000
1.000 0.0271 0.01814 0.00697 0.0142 1.0000 1.0000
1.250 0.0335 0.01828 0.00709 0.0169 1.0000 1.0000
1.500 0.0659 0.01851 0.00739 0.0146 0.9921 1.0000
1.750 0.1042 0.01876 0.00774 0.0113 0.9812 1.0000
2.000 0.1429 0.01901 0.00816 0.0081 0.9699 1.0000
2.250 0.1825 0.01927 0.00859 0.0049 0.9579 1.0000
2.500 0.2233 0.01951 0.00906 0.0016 0.9452 1.0000
2.750 0.2651 0.01974 0.00964 -0.0018 0.9318 1.0000
3.000 0.3079 0.01993 0.01019 -0.0051 0.9177 1.0000
3.250 0.4303 0.01779 0.00871 -0.0150 0.7435 1.0000
3.500 0.4298 0.01986 0.00809 -0.0069 0.2146 1.0000
3.750 0.4399 0.02200 0.00942 -0.0046 0.1029 1.0000
4.000 0.4560 0.02323 0.01057 -0.0028 0.0800 1.0000
4.250 0.4725 0.02449 0.01186 -0.0009 0.0716 1.0000
4.500 0.4921 0.02565 0.01326 0.0009 0.0660 1.0000
4.750 0.5135 0.02719 0.01479 0.0020 0.0588 1.0000
5.000 0.5389 0.02849 0.01635 0.0030 0.0525 1.0000
5.250 0.5664 0.03033 0.01847 0.0036 0.0498 1.0000
5.500 0.5924 0.03246 0.02080 0.0042 0.0479 1.0000
5.750 0.6162 0.03493 0.02352 0.0051 0.0467 1.0000
6.000 0.6366 0.03789 0.02674 0.0062 0.0452 1.0000
6.250 0.6543 0.03994 0.02940 0.0083 0.0432 1.0000
6.500 0.6700 0.04246 0.03245 0.0103 0.0411 1.0000
6.750 0.6836 0.04541 0.03586 0.0123 0.0406 1.0000
7.000 0.6949 0.04864 0.03952 0.0142 0.0407 1.0000
7.250 0.7036 0.05206 0.04335 0.0162 0.0410 1.0000
7.500 0.7099 0.05565 0.04731 0.0180 0.0414 1.0000
7.750 0.7137 0.05939 0.05146 0.0197 0.0419 1.0000
8.000 0.7152 0.06324 0.05558 0.0210 0.0424 1.0000
8.250 0.7146 0.06717 0.05974 0.0222 0.0430 1.0000
8.500 0.7122 0.07118 0.06391 0.0230 0.0436 1.0000
8.750 0.7093 0.07527 0.06811 0.0235 0.0443 1.0000
9.000 0.7101 0.07963 0.07250 0.0239 0.0450 1.0000
9.250 0.6928 0.08315 0.07627 0.0238 0.0468 1.0000
9.500 0.6691 0.08897 0.08215 0.0197 0.0486 1.0000
9.750 0.6568 0.09590 0.08898 0.0138 0.0505 1.0000
10.000 0.6516 0.10210 0.09513 0.0094 0.0526 1.0000
10.250 0.6501 0.10733 0.10031 0.0069 0.0549 1.0000
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Polar data table (+)
Polar graphs
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