DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DSMA-523B AIRFOIL (dsma523b-il) Reynolds number: 50,000 Max Cl/Cd: 20.63 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dsma523b-il-50000-n5.txt Download as CSV file: xf-dsma523b-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7782 0.07377 0.06479 -0.0466 1.0000 0.0704
-10.000 -0.7980 0.06841 0.05921 -0.0486 1.0000 0.0704
-9.750 -0.8061 0.06375 0.05430 -0.0501 1.0000 0.0708
-9.500 -0.7964 0.06131 0.05182 -0.0498 1.0000 0.0719
-9.250 -0.7899 0.05806 0.04839 -0.0505 1.0000 0.0731
-9.000 -0.7814 0.05453 0.04457 -0.0516 1.0000 0.0744
-8.750 -0.7692 0.05083 0.04047 -0.0529 1.0000 0.0756
-8.500 -0.7526 0.04728 0.03647 -0.0542 1.0000 0.0767
-8.250 -0.7325 0.04406 0.03275 -0.0553 1.0000 0.0779
-8.000 -0.7116 0.04224 0.03088 -0.0552 1.0000 0.0798
-7.750 -0.6896 0.04058 0.02911 -0.0552 1.0000 0.0824
-7.500 -0.6662 0.03864 0.02688 -0.0554 1.0000 0.0854
-7.250 -0.6433 0.03699 0.02508 -0.0550 1.0000 0.0877
-7.000 -0.6208 0.03572 0.02377 -0.0543 1.0000 0.0902
-6.750 -0.5976 0.03453 0.02245 -0.0536 1.0000 0.0942
-6.500 -0.5751 0.03345 0.02129 -0.0526 1.0000 0.0983
-6.250 -0.5534 0.03255 0.02043 -0.0513 1.0000 0.1023
-6.000 -0.5315 0.03177 0.01950 -0.0497 1.0000 0.1073
-5.750 -0.5100 0.03100 0.01881 -0.0484 1.0000 0.1130
-5.500 -0.4878 0.03029 0.01809 -0.0471 1.0000 0.1197
-5.250 -0.4651 0.02956 0.01742 -0.0462 1.0000 0.1275
-5.000 -0.4413 0.02887 0.01672 -0.0456 1.0000 0.1383
-4.750 -0.4161 0.02805 0.01608 -0.0456 1.0000 0.1524
-4.500 -0.3889 0.02716 0.01538 -0.0462 1.0000 0.1741
-4.250 -0.3580 0.02598 0.01465 -0.0481 1.0000 0.2195
-4.000 -0.3230 0.02460 0.01405 -0.0514 1.0000 0.3209
-3.750 -0.3107 0.02461 0.01498 -0.0467 1.0000 0.4347
-3.500 -0.3142 0.02594 0.01677 -0.0365 1.0000 0.5025
-3.250 -0.2936 0.02683 0.01763 -0.0337 1.0000 0.5787
-3.000 -0.2551 0.02729 0.01783 -0.0368 1.0000 0.6336
-2.750 -0.2301 0.02784 0.01825 -0.0358 1.0000 0.6602
-2.500 -0.2043 0.02839 0.01869 -0.0351 1.0000 0.6862
-2.250 -0.1877 0.02882 0.01908 -0.0318 1.0000 0.7057
-2.000 -0.1709 0.02912 0.01936 -0.0287 1.0000 0.7243
-1.750 -0.1567 0.02929 0.01952 -0.0249 1.0000 0.7417
-1.500 -0.1436 0.02937 0.01961 -0.0210 1.0000 0.7599
-1.250 -0.1306 0.02933 0.01959 -0.0171 1.0000 0.7780
-1.000 -0.1170 0.02916 0.01944 -0.0136 1.0000 0.7937
-0.750 -0.1000 0.02895 0.01923 -0.0111 1.0000 0.8070
-0.500 -0.0760 0.02886 0.01913 -0.0107 1.0000 0.8182
-0.250 -0.0561 0.02860 0.01889 -0.0093 1.0000 0.8257
0.000 -0.0280 0.02856 0.01886 -0.0101 1.0000 0.8314
0.250 -0.0007 0.02851 0.01885 -0.0107 1.0000 0.8358
0.500 0.0238 0.02841 0.01880 -0.0106 1.0000 0.8399
0.750 0.0506 0.02843 0.01889 -0.0111 1.0000 0.8439
1.000 0.0796 0.02855 0.01909 -0.0123 1.0000 0.8471
1.250 0.1099 0.02875 0.01939 -0.0138 1.0000 0.8500
1.500 0.1362 0.02886 0.01965 -0.0143 1.0000 0.8525
1.750 0.1626 0.02905 0.01999 -0.0149 1.0000 0.8547
2.000 0.2514 0.02848 0.01965 -0.0262 0.9524 0.8557
2.250 0.3084 0.02663 0.01800 -0.0296 0.8782 0.8571
2.500 0.3346 0.02588 0.01743 -0.0281 0.7987 0.8589
2.750 0.4382 0.02650 0.01522 -0.0381 0.2733 0.8590
3.000 0.4651 0.02771 0.01584 -0.0386 0.1955 0.8606
3.250 0.4955 0.02867 0.01651 -0.0396 0.1648 0.8623
3.500 0.5281 0.02956 0.01726 -0.0409 0.1469 0.8639
3.750 0.5631 0.03037 0.01810 -0.0425 0.1339 0.8651
4.000 0.6006 0.03130 0.01903 -0.0445 0.1238 0.8659
4.250 0.6364 0.03223 0.02000 -0.0461 0.1166 0.8667
4.500 0.6710 0.03336 0.02106 -0.0476 0.1103 0.8678
4.750 0.7039 0.03441 0.02229 -0.0485 0.1044 0.8692
5.000 0.7362 0.03568 0.02366 -0.0494 0.1005 0.8708
5.250 0.7675 0.03721 0.02513 -0.0505 0.0968 0.8723
5.500 0.7974 0.03874 0.02699 -0.0510 0.0928 0.8736
5.750 0.8264 0.04044 0.02901 -0.0514 0.0894 0.8747
6.000 0.8546 0.04238 0.03120 -0.0518 0.0872 0.8756
6.250 0.8810 0.04428 0.03328 -0.0522 0.0848 0.8765
6.500 0.9066 0.04652 0.03553 -0.0527 0.0824 0.8774
6.750 0.9257 0.04902 0.03870 -0.0517 0.0801 0.8785
7.000 0.9432 0.05193 0.04213 -0.0507 0.0785 0.8798
7.250 0.9564 0.05501 0.04569 -0.0492 0.0776 0.8811
7.500 0.9665 0.05829 0.04942 -0.0475 0.0767 0.8825
7.750 0.9738 0.06167 0.05321 -0.0459 0.0756 0.8839
8.000 0.9795 0.06502 0.05691 -0.0443 0.0744 0.8851
8.250 0.9850 0.06821 0.06036 -0.0430 0.0731 0.8862
8.500 0.9906 0.07138 0.06375 -0.0420 0.0720 0.8871
8.750 0.9972 0.07453 0.06703 -0.0411 0.0711 0.8880
9.000 0.9911 0.07875 0.07153 -0.0397 0.0709 0.8888
9.250 0.9601 0.08429 0.07749 -0.0373 0.0713 0.8894
9.500 0.9123 0.09252 0.08610 -0.0378 0.0725 0.8898
9.750 0.8656 0.10456 0.09839 -0.0454 0.0742 0.8900
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Polar data table (+)
Polar graphs
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