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DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
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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