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DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DSMA-523B AIRFOIL (dsma523b-il)
Reynolds number: 100,000
Max Cl/Cd: 23.34 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dsma523b-il-100000.txt
Download as CSV file: xf-dsma523b-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5589   0.10034   0.09466  -0.0156   1.0000   0.1893
  -8.750  -0.7755   0.05484   0.04758  -0.0538   1.0000   0.0969
  -8.500  -0.7587   0.05064   0.04321  -0.0547   1.0000   0.0960
  -8.250  -0.7396   0.04641   0.03871  -0.0562   1.0000   0.0953
  -8.000  -0.7170   0.04239   0.03436  -0.0580   1.0000   0.0944
  -7.750  -0.6909   0.03865   0.03022  -0.0600   1.0000   0.0935
  -7.500  -0.6626   0.03555   0.02669  -0.0617   1.0000   0.0936
  -7.250  -0.6329   0.03320   0.02391  -0.0632   1.0000   0.0953
  -7.000  -0.6042   0.03112   0.02154  -0.0642   1.0000   0.0978
  -6.750  -0.5785   0.02962   0.02003  -0.0643   1.0000   0.1005
  -6.500  -0.5516   0.02827   0.01859  -0.0642   1.0000   0.1031
  -6.250  -0.5237   0.02713   0.01728  -0.0643   1.0000   0.1070
  -6.000  -0.4973   0.02588   0.01601  -0.0642   1.0000   0.1115
  -5.750  -0.4708   0.02497   0.01517  -0.0639   1.0000   0.1165
  -5.500  -0.4429   0.02420   0.01430  -0.0638   1.0000   0.1223
  -5.250  -0.4166   0.02327   0.01356  -0.0636   1.0000   0.1298
  -5.000  -0.3884   0.02268   0.01295  -0.0635   1.0000   0.1386
  -4.750  -0.3606   0.02193   0.01244  -0.0637   1.0000   0.1501
  -4.500  -0.3313   0.02130   0.01199  -0.0640   1.0000   0.1658
  -4.250  -0.2997   0.02062   0.01160  -0.0649   1.0000   0.1979
  -4.000  -0.2590   0.01909   0.01225  -0.0682   1.0000   0.4803
  -3.750  -0.2712   0.02082   0.01441  -0.0559   1.0000   0.5581
  -3.500  -0.2370   0.02181   0.01518  -0.0570   1.0000   0.6318
  -3.250  -0.2223   0.02282   0.01613  -0.0528   1.0000   0.6538
  -3.000  -0.2057   0.02360   0.01686  -0.0493   1.0000   0.6720
  -2.750  -0.1899   0.02427   0.01749  -0.0456   1.0000   0.6890
  -2.500  -0.1694   0.02476   0.01792  -0.0434   1.0000   0.7052
  -2.250  -0.1628   0.02510   0.01829  -0.0374   1.0000   0.7148
  -2.000  -0.1469   0.02538   0.01855  -0.0341   1.0000   0.7294
  -1.750  -0.1285   0.02562   0.01878  -0.0316   1.0000   0.7450
  -1.500  -0.1153   0.02574   0.01891  -0.0277   1.0000   0.7587
  -1.250  -0.1048   0.02572   0.01891  -0.0232   1.0000   0.7722
  -1.000  -0.0914   0.02569   0.01891  -0.0196   1.0000   0.7878
  -0.750  -0.0797   0.02561   0.01885  -0.0155   1.0000   0.8052
  -0.500  -0.0683   0.02544   0.01871  -0.0116   1.0000   0.8228
  -0.250  -0.0556   0.02521   0.01852  -0.0081   1.0000   0.8396
   0.000  -0.0364   0.02505   0.01838  -0.0064   1.0000   0.8531
   0.250  -0.0159   0.02489   0.01825  -0.0051   1.0000   0.8639
   0.500   0.0021   0.02461   0.01802  -0.0034   1.0000   0.8732
   0.750   0.0261   0.02455   0.01801  -0.0032   1.0000   0.8822
   1.000   0.0488   0.02448   0.01801  -0.0027   1.0000   0.8910
   1.250   0.0690   0.02434   0.01793  -0.0018   1.0000   0.8990
   1.500   0.0930   0.02436   0.01805  -0.0018   1.0000   0.9060
   1.750   0.1185   0.02450   0.01829  -0.0022   1.0000   0.9114
   2.000   0.2150   0.02384   0.01778  -0.0147   0.9639   0.9158
   2.250   0.2846   0.02204   0.01617  -0.0211   0.9268   0.9176
   2.500   0.3336   0.02016   0.01448  -0.0227   0.8653   0.9185
   2.750   0.4398   0.02161   0.01223  -0.0335   0.1837   0.9199
   3.000   0.4681   0.02243   0.01286  -0.0339   0.1624   0.9213
   3.250   0.4979   0.02335   0.01359  -0.0347   0.1485   0.9223
   3.500   0.5300   0.02403   0.01427  -0.0357   0.1381   0.9227
   3.750   0.5631   0.02515   0.01520  -0.0371   0.1305   0.9235
   4.000   0.5961   0.02611   0.01624  -0.0381   0.1248   0.9248
   4.250   0.6285   0.02700   0.01719  -0.0392   0.1184   0.9258
   4.500   0.6630   0.02841   0.01854  -0.0408   0.1141   0.9261
   4.750   0.6971   0.03036   0.02061  -0.0423   0.1109   0.9264
   5.000   0.7273   0.03150   0.02207  -0.0427   0.1073   0.9273
   5.250   0.7573   0.03309   0.02392  -0.0432   0.1046   0.9283
   5.500   0.7866   0.03508   0.02622  -0.0436   0.1031   0.9289
   5.750   0.8146   0.03713   0.02853  -0.0439   0.1014   0.9290
   6.000   0.8429   0.03917   0.03063  -0.0447   0.0987   0.9292
   6.250   0.8674   0.04225   0.03393  -0.0449   0.0973   0.9294
   6.500   0.8792   0.04650   0.03931  -0.0418   0.1026   0.9295
   6.750   0.8858   0.05365   0.04739  -0.0390   0.1184   0.9297
   7.000   0.8444   0.07323   0.06877  -0.0382   0.2134   0.9295
   7.250   0.8298   0.07781   0.07354  -0.0379   0.2022   0.9296
   7.500   0.8369   0.08094   0.07675  -0.0378   0.1939   0.9302
   7.750   0.8989   0.08800   0.08332  -0.0391   0.1879   0.9315
   8.000   0.8057   0.09050   0.08646  -0.0388   0.1817   0.9311
   8.250   0.7955   0.09534   0.09137  -0.0414   0.1749   0.9312
   8.500   0.9086   0.09994   0.09553  -0.0389   0.1675   0.9323
   8.750   0.8208   0.10388   0.09987  -0.0409   0.1659   0.9315
   9.000   0.7709   0.11317   0.10918  -0.0548   0.1581   0.9311
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