DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DSMA-523B AIRFOIL (dsma523b-il) Reynolds number: 200,000 Max Cl/Cd: 29.75 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dsma523b-il-200000.txt Download as CSV file: xf-dsma523b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: DSMA-523B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6224 0.09817 0.09405 -0.0262 1.0000 0.0891
-10.000 -0.8806 0.05190 0.04593 -0.0549 1.0000 0.0572
-9.750 -0.8626 0.04908 0.04326 -0.0536 1.0000 0.0565
-9.500 -0.8491 0.04516 0.03909 -0.0547 1.0000 0.0562
-9.250 -0.8316 0.04128 0.03479 -0.0567 1.0000 0.0562
-9.000 -0.8089 0.03784 0.03086 -0.0589 1.0000 0.0564
-8.750 -0.7829 0.03504 0.02761 -0.0608 1.0000 0.0566
-8.500 -0.7540 0.03300 0.02507 -0.0627 1.0000 0.0571
-8.250 -0.7306 0.03045 0.02248 -0.0628 1.0000 0.0579
-8.000 -0.7071 0.02894 0.02101 -0.0625 1.0000 0.0590
-7.750 -0.6810 0.02770 0.01968 -0.0628 1.0000 0.0608
-7.500 -0.6521 0.02655 0.01825 -0.0636 1.0000 0.0627
-7.250 -0.6246 0.02515 0.01667 -0.0640 1.0000 0.0643
-7.000 -0.5996 0.02393 0.01551 -0.0636 1.0000 0.0660
-6.750 -0.5730 0.02302 0.01460 -0.0635 1.0000 0.0680
-6.500 -0.5444 0.02234 0.01378 -0.0638 1.0000 0.0704
-6.250 -0.5192 0.02124 0.01288 -0.0634 1.0000 0.0734
-6.000 -0.4911 0.02060 0.01226 -0.0637 1.0000 0.0766
-5.750 -0.4621 0.01984 0.01158 -0.0641 1.0000 0.0797
-5.500 -0.4316 0.01933 0.01116 -0.0651 1.0000 0.0842
-5.250 -0.3994 0.01879 0.01070 -0.0664 1.0000 0.0893
-5.000 -0.3673 0.01843 0.01038 -0.0677 1.0000 0.0951
-4.750 -0.3328 0.01798 0.01003 -0.0696 1.0000 0.1025
-4.500 -0.2982 0.01762 0.00972 -0.0714 1.0000 0.1118
-4.250 -0.2617 0.01724 0.00945 -0.0738 1.0000 0.1258
-4.000 -0.2188 0.01663 0.00917 -0.0779 1.0000 0.1690
-3.750 -0.1409 0.01494 0.00890 -0.0911 1.0000 0.4412
-3.500 -0.1374 0.01580 0.01053 -0.0841 1.0000 0.5588
-3.250 -0.1134 0.01629 0.01101 -0.0830 1.0000 0.6113
-3.000 -0.0892 0.01678 0.01146 -0.0819 1.0000 0.6328
-2.750 -0.0656 0.01733 0.01195 -0.0806 1.0000 0.6495
-2.500 -0.0510 0.01792 0.01258 -0.0770 1.0000 0.6558
-2.250 -0.0218 0.01826 0.01286 -0.0773 1.0000 0.6677
-2.000 -0.0073 0.01876 0.01341 -0.0737 1.0000 0.6720
-1.750 0.0123 0.01919 0.01386 -0.0716 1.0000 0.6788
-1.500 0.0393 0.01950 0.01415 -0.0714 1.0000 0.6875
-1.250 0.0530 0.01994 0.01467 -0.0678 1.0000 0.6920
-1.000 0.0739 0.02039 0.01515 -0.0660 1.0000 0.7015
-0.750 0.0848 0.02091 0.01575 -0.0616 1.0000 0.7100
-0.500 0.1018 0.02154 0.01644 -0.0588 1.0000 0.7250
-0.250 0.1042 0.02197 0.01698 -0.0523 1.0000 0.7330
0.000 0.1363 0.02231 0.01735 -0.0531 0.9977 0.7448
0.250 0.1963 0.02203 0.01714 -0.0580 0.9826 0.7508
0.500 0.2674 0.02139 0.01654 -0.0658 0.9672 0.7584
0.750 0.3050 0.02059 0.01582 -0.0668 0.9490 0.7648
1.000 0.3426 0.01937 0.01469 -0.0667 0.9302 0.7723
1.250 0.4669 0.01777 0.01154 -0.0820 0.5268 0.7841
1.500 0.4688 0.01948 0.01190 -0.0767 0.2555 0.7884
1.750 0.4898 0.02058 0.01232 -0.0756 0.1430 0.7939
2.000 0.5235 0.02127 0.01282 -0.0774 0.1206 0.7995
2.250 0.5389 0.02147 0.01294 -0.0743 0.1111 0.8029
2.500 0.5642 0.02173 0.01320 -0.0737 0.1043 0.8052
2.750 0.5917 0.02235 0.01371 -0.0738 0.0975 0.8065
3.000 0.6220 0.02283 0.01419 -0.0745 0.0926 0.8074
3.250 0.6519 0.02333 0.01467 -0.0751 0.0883 0.8091
3.500 0.6827 0.02407 0.01533 -0.0759 0.0845 0.8106
3.750 0.7153 0.02509 0.01633 -0.0772 0.0809 0.8113
4.000 0.7478 0.02565 0.01695 -0.0782 0.0778 0.8118
4.250 0.7804 0.02642 0.01775 -0.0794 0.0751 0.8128
4.500 0.8131 0.02733 0.01861 -0.0807 0.0723 0.8140
4.750 0.8462 0.02897 0.02029 -0.0821 0.0696 0.8146
5.000 0.8775 0.02976 0.02127 -0.0828 0.0677 0.8148
5.250 0.9088 0.03094 0.02264 -0.0836 0.0659 0.8152
5.500 0.9404 0.03233 0.02418 -0.0845 0.0643 0.8162
5.750 0.9710 0.03378 0.02575 -0.0853 0.0631 0.8168
6.000 0.9988 0.03518 0.02722 -0.0857 0.0617 0.8170
6.250 1.0235 0.03832 0.03050 -0.0858 0.0603 0.8172
6.500 1.0453 0.03984 0.03244 -0.0846 0.0593 0.8174
6.750 1.0656 0.04242 0.03541 -0.0834 0.0591 0.8176
7.000 1.0828 0.04551 0.03891 -0.0819 0.0591 0.8179
7.250 1.0973 0.04896 0.04273 -0.0802 0.0592 0.8181
7.500 1.1086 0.05265 0.04679 -0.0781 0.0593 0.8183
7.750 1.1190 0.05714 0.05152 -0.0765 0.0598 0.8186
8.000 1.0575 0.07538 0.07142 -0.0662 0.0845 0.8184
8.250 1.0735 0.07892 0.07490 -0.0660 0.0836 0.8191
8.500 1.0665 0.08852 0.08452 -0.0658 0.0823 0.8196
8.750 1.0444 0.09186 0.08820 -0.0624 0.0820 0.8199
9.000 0.9955 0.09564 0.09231 -0.0582 0.0815 0.8197
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Polar data table (+)
Polar graphs
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