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DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
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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