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DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DSMA-523A AIRFOIL (dsma523a-il)
Reynolds number: 200,000
Max Cl/Cd: 37.4 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dsma523a-il-200000-n5.txt
Download as CSV file: xf-dsma523a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DSMA-523A 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8637   0.07519   0.07022  -0.0502   1.0000   0.0303
 -13.000  -0.9094   0.06526   0.05999  -0.0557   1.0000   0.0302
 -12.750  -0.9392   0.05908   0.05356  -0.0576   1.0000   0.0302
 -12.500  -0.9621   0.05437   0.04860  -0.0579   1.0000   0.0304
 -12.250  -0.9807   0.05051   0.04451  -0.0572   1.0000   0.0305
 -12.000  -0.9962   0.04726   0.04104  -0.0557   1.0000   0.0307
 -11.750  -1.0099   0.04451   0.03806  -0.0534   1.0000   0.0310
 -11.500  -1.0228   0.04219   0.03552  -0.0504   1.0000   0.0312
 -11.250  -1.0282   0.03972   0.03279  -0.0485   1.0000   0.0315
 -11.000  -1.0235   0.03780   0.03071  -0.0473   1.0000   0.0318
 -10.750  -1.0133   0.03645   0.02930  -0.0465   1.0000   0.0321
 -10.500  -1.0010   0.03521   0.02799  -0.0458   1.0000   0.0324
 -10.250  -0.9871   0.03402   0.02672  -0.0453   1.0000   0.0328
 -10.000  -0.9717   0.03290   0.02551  -0.0448   1.0000   0.0332
  -9.750  -0.9553   0.03181   0.02430  -0.0442   1.0000   0.0339
  -9.500  -0.9381   0.03063   0.02299  -0.0437   1.0000   0.0346
  -9.250  -0.9200   0.02937   0.02153  -0.0431   1.0000   0.0356
  -9.000  -0.9009   0.02819   0.02019  -0.0425   1.0000   0.0364
  -8.750  -0.8799   0.02749   0.01948  -0.0422   1.0000   0.0370
  -8.500  -0.8581   0.02681   0.01876  -0.0420   1.0000   0.0377
  -8.250  -0.8360   0.02608   0.01797  -0.0417   1.0000   0.0385
  -8.000  -0.8133   0.02532   0.01712  -0.0414   1.0000   0.0397
  -7.750  -0.7904   0.02450   0.01613  -0.0410   1.0000   0.0412
  -7.500  -0.7665   0.02395   0.01561  -0.0410   1.0000   0.0421
  -7.250  -0.7421   0.02341   0.01505  -0.0410   1.0000   0.0433
  -7.000  -0.7176   0.02281   0.01439  -0.0408   1.0000   0.0448
  -6.750  -0.6928   0.02219   0.01365  -0.0406   1.0000   0.0464
  -6.500  -0.6679   0.02161   0.01311  -0.0406   1.0000   0.0476
  -6.250  -0.6423   0.02110   0.01260  -0.0406   1.0000   0.0493
  -6.000  -0.6159   0.02068   0.01208  -0.0407   1.0000   0.0517
  -5.750  -0.5898   0.02010   0.01155  -0.0409   1.0000   0.0536
  -5.500  -0.5629   0.01957   0.01104  -0.0412   1.0000   0.0559
  -5.250  -0.5354   0.01920   0.01059  -0.0415   1.0000   0.0583
  -5.000  -0.5064   0.01847   0.00998  -0.0425   1.0000   0.0609
  -4.750  -0.4768   0.01800   0.00951  -0.0434   1.0000   0.0638
  -4.500  -0.4452   0.01743   0.00899  -0.0449   1.0000   0.0666
  -4.250  -0.4128   0.01696   0.00854  -0.0464   0.9999   0.0697
  -4.000  -0.3781   0.01658   0.00819  -0.0484   0.9992   0.0733
  -3.750  -0.3439   0.01624   0.00792  -0.0502   0.9987   0.0774
  -3.500  -0.3093   0.01595   0.00773  -0.0521   0.9980   0.0838
  -3.250  -0.2738   0.01569   0.00759  -0.0541   0.9972   0.0995
  -3.000  -0.2372   0.01536   0.00746  -0.0565   0.9966   0.1298
  -2.750  -0.1997   0.01499   0.00734  -0.0592   0.9962   0.1751
  -2.500  -0.1614   0.01465   0.00724  -0.0620   0.9958   0.2244
  -2.250  -0.1189   0.01409   0.00711  -0.0660   0.9961   0.3123
  -2.000  -0.0723   0.01333   0.00715  -0.0710   0.9973   0.4752
  -1.750  -0.0567   0.01437   0.00881  -0.0666   0.9938   0.5694
  -1.500  -0.0305   0.01482   0.00933  -0.0657   0.9903   0.6027
  -1.250   0.0064   0.01493   0.00940  -0.0677   0.9884   0.6224
  -1.000   0.0522   0.01507   0.00948  -0.0717   0.9857   0.6454
  -0.500   0.1427   0.01595   0.01043  -0.0762   0.9610   0.6803
  -0.250   0.1593   0.01575   0.01031  -0.0725   0.9408   0.6838
   0.000   0.2064   0.01517   0.00976  -0.0748   0.9262   0.6875
   0.250   0.2456   0.01469   0.00929  -0.0760   0.9035   0.6911
   0.500   0.2708   0.01444   0.00903  -0.0753   0.8653   0.6953
   0.750   0.3657   0.01531   0.00805  -0.0868   0.4562   0.6991
   1.000   0.3808   0.01621   0.00838  -0.0840   0.3305   0.7011
   1.250   0.4003   0.01690   0.00866  -0.0822   0.2383   0.7034
   1.500   0.4222   0.01751   0.00892  -0.0809   0.1617   0.7063
   1.750   0.4474   0.01801   0.00916  -0.0804   0.1184   0.7100
   2.000   0.4792   0.01834   0.00933  -0.0816   0.0994   0.7148
   2.500   0.5311   0.01890   0.00981  -0.0806   0.0837   0.7186
   2.750   0.5579   0.01918   0.01005  -0.0804   0.0780   0.7193
   3.000   0.5850   0.01946   0.01031  -0.0803   0.0736   0.7201
   3.250   0.6123   0.01972   0.01058  -0.0802   0.0697   0.7208
   3.500   0.6392   0.02006   0.01089  -0.0800   0.0667   0.7216
   3.750   0.6661   0.02047   0.01127  -0.0799   0.0640   0.7224
   4.000   0.6937   0.02078   0.01161  -0.0799   0.0612   0.7232
   4.250   0.7209   0.02113   0.01195  -0.0798   0.0586   0.7243
   4.500   0.7476   0.02159   0.01237  -0.0797   0.0567   0.7255
   4.750   0.7749   0.02211   0.01291  -0.0796   0.0549   0.7266
   5.000   0.8029   0.02254   0.01338  -0.0797   0.0529   0.7275
   5.250   0.8309   0.02297   0.01382  -0.0799   0.0509   0.7283
   5.500   0.8586   0.02344   0.01427  -0.0800   0.0493   0.7292
   5.750   0.8857   0.02416   0.01494  -0.0801   0.0480   0.7301
   6.000   0.9138   0.02479   0.01568  -0.0802   0.0468   0.7310
   6.250   0.9417   0.02548   0.01646  -0.0803   0.0455   0.7318
   6.500   0.9692   0.02612   0.01717  -0.0804   0.0441   0.7327
   6.750   0.9963   0.02671   0.01777  -0.0805   0.0428   0.7335
   7.000   1.0232   0.02736   0.01839  -0.0806   0.0418   0.7346
   7.250   1.0480   0.02827   0.01938  -0.0802   0.0408   0.7354
   7.500   1.0722   0.02926   0.02058  -0.0795   0.0400   0.7361
   7.750   1.0959   0.03032   0.02184  -0.0788   0.0390   0.7367
   8.000   1.1190   0.03137   0.02305  -0.0781   0.0381   0.7373
   8.250   1.1415   0.03233   0.02415  -0.0773   0.0373   0.7379
   8.500   1.1636   0.03317   0.02509  -0.0765   0.0366   0.7385
   8.750   1.1852   0.03400   0.02597  -0.0757   0.0360   0.7391
   9.000   1.2062   0.03501   0.02702  -0.0749   0.0354   0.7398
   9.250   1.2234   0.03672   0.02907  -0.0734   0.0347   0.7404
   9.500   1.2380   0.03878   0.03150  -0.0716   0.0340   0.7411
   9.750   1.2501   0.04101   0.03408  -0.0696   0.0334   0.7418
  10.000   1.2597   0.04334   0.03674  -0.0674   0.0329   0.7425
  10.250   1.2665   0.04574   0.03946  -0.0650   0.0324   0.7432
  10.500   1.2703   0.04822   0.04223  -0.0623   0.0320   0.7440
  10.750   1.2701   0.05084   0.04513  -0.0593   0.0317   0.7449
  11.000   1.2645   0.05340   0.04795  -0.0558   0.0315   0.7459
  11.250   1.2522   0.05629   0.05108  -0.0519   0.0313   0.7468
  11.500   1.2361   0.05971   0.05476  -0.0485   0.0311   0.7476
  11.750   1.2116   0.06418   0.05952  -0.0458   0.0310   0.7481
  12.000   1.1702   0.07133   0.06702  -0.0453   0.0310   0.7485
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