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DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DSMA-523A AIRFOIL (dsma523a-il)
Reynolds number: 100,000
Max Cl/Cd: 25.7 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dsma523a-il-100000-n5.txt
Download as CSV file: xf-dsma523a-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6691   0.10297   0.09668  -0.0333   1.0000   0.0464
 -11.750  -0.7119   0.08808   0.08170  -0.0425   1.0000   0.0459
 -11.500  -0.7571   0.07707   0.07053  -0.0494   1.0000   0.0455
 -11.250  -0.7929   0.07006   0.06335  -0.0522   1.0000   0.0453
 -11.000  -0.8230   0.06496   0.05806  -0.0528   1.0000   0.0452
 -10.750  -0.8497   0.06105   0.05398  -0.0516   1.0000   0.0451
 -10.500  -0.8747   0.05792   0.05069  -0.0492   1.0000   0.0451
 -10.250  -0.8903   0.05429   0.04681  -0.0485   1.0000   0.0453
 -10.000  -0.8984   0.05076   0.04295  -0.0481   1.0000   0.0456
  -9.750  -0.9002   0.04747   0.03926  -0.0476   1.0000   0.0460
  -9.500  -0.8964   0.04436   0.03569  -0.0472   1.0000   0.0465
  -9.250  -0.8818   0.04259   0.03386  -0.0466   1.0000   0.0472
  -9.000  -0.8660   0.04102   0.03221  -0.0460   1.0000   0.0481
  -8.750  -0.8502   0.03925   0.03026  -0.0456   1.0000   0.0493
  -8.500  -0.8333   0.03732   0.02800  -0.0454   1.0000   0.0507
  -8.250  -0.8145   0.03539   0.02563  -0.0454   1.0000   0.0520
  -8.000  -0.7942   0.03382   0.02395  -0.0448   1.0000   0.0529
  -7.750  -0.7734   0.03248   0.02258  -0.0441   1.0000   0.0540
  -7.500  -0.7519   0.03120   0.02120  -0.0435   1.0000   0.0554
  -7.250  -0.7295   0.03002   0.01980  -0.0431   1.0000   0.0574
  -7.000  -0.7074   0.02887   0.01855  -0.0424   1.0000   0.0593
  -6.750  -0.6856   0.02783   0.01755  -0.0416   1.0000   0.0614
  -6.500  -0.6631   0.02688   0.01654  -0.0409   1.0000   0.0635
  -6.250  -0.6405   0.02596   0.01557  -0.0400   1.0000   0.0654
  -6.000  -0.6184   0.02503   0.01478  -0.0393   1.0000   0.0679
  -5.750  -0.5948   0.02425   0.01399  -0.0389   1.0000   0.0710
  -5.500  -0.5707   0.02342   0.01326  -0.0387   1.0000   0.0739
  -5.250  -0.5453   0.02272   0.01262  -0.0387   1.0000   0.0770
  -5.000  -0.5189   0.02207   0.01202  -0.0390   1.0000   0.0810
  -4.750  -0.4919   0.02154   0.01154  -0.0394   1.0000   0.0859
  -4.500  -0.4644   0.02104   0.01110  -0.0398   1.0000   0.0912
  -4.250  -0.4367   0.02063   0.01072  -0.0401   1.0000   0.0988
  -4.000  -0.4085   0.02019   0.01036  -0.0406   1.0000   0.1089
  -3.750  -0.3801   0.01977   0.01008  -0.0411   1.0000   0.1246
  -3.500  -0.3511   0.01930   0.00986  -0.0418   1.0000   0.1552
  -3.250  -0.3191   0.01873   0.00963  -0.0434   1.0000   0.2111
  -3.000  -0.2797   0.01786   0.00935  -0.0471   1.0000   0.3133
  -2.750  -0.2523   0.01750   0.01001  -0.0470   1.0000   0.4713
  -2.500  -0.2633   0.01900   0.01200  -0.0357   1.0000   0.5293
  -2.250  -0.2476   0.01975   0.01281  -0.0321   1.0000   0.5862
  -2.000  -0.2058   0.01967   0.01257  -0.0362   1.0000   0.6226
  -1.750  -0.1678   0.01976   0.01253  -0.0391   1.0000   0.6456
  -1.250  -0.1204   0.02071   0.01344  -0.0368   1.0000   0.6752
  -1.000  -0.1039   0.02130   0.01407  -0.0338   1.0000   0.6882
  -0.750  -0.0872   0.02187   0.01468  -0.0308   1.0000   0.7027
  -0.500  -0.0663   0.02235   0.01518  -0.0291   1.0000   0.7173
  -0.250  -0.0539   0.02263   0.01552  -0.0253   1.0000   0.7236
   0.000  -0.0283   0.02275   0.01566  -0.0251   1.0000   0.7294
   0.250   0.0153   0.02308   0.01601  -0.0283   0.9938   0.7369
   0.500   0.0621   0.02339   0.01638  -0.0309   0.9790   0.7434
   0.750   0.1172   0.02341   0.01644  -0.0358   0.9628   0.7512
   1.000   0.1529   0.02287   0.01598  -0.0366   0.9412   0.7560
   1.250   0.2068   0.02188   0.01505  -0.0395   0.9137   0.7601
   1.500   0.2316   0.02128   0.01453  -0.0379   0.8775   0.7635
   1.750   0.2574   0.02079   0.01410  -0.0370   0.8310   0.7656
   2.000   0.3702   0.02100   0.01228  -0.0501   0.3908   0.7647
   2.250   0.3978   0.02196   0.01246  -0.0507   0.2415   0.7667
   2.500   0.4263   0.02269   0.01268  -0.0514   0.1594   0.7686
   2.750   0.4557   0.02319   0.01296  -0.0522   0.1285   0.7699
   3.000   0.4859   0.02366   0.01331  -0.0532   0.1140   0.7715
   3.500   0.5377   0.02447   0.01403  -0.0527   0.0971   0.7738
   3.750   0.5636   0.02494   0.01448  -0.0525   0.0919   0.7746
   4.000   0.5897   0.02555   0.01504  -0.0524   0.0874   0.7754
   4.250   0.6171   0.02604   0.01557  -0.0525   0.0827   0.7761
   4.500   0.6443   0.02663   0.01614  -0.0526   0.0789   0.7769
   4.750   0.6718   0.02755   0.01695  -0.0528   0.0761   0.7778
   5.000   0.7003   0.02821   0.01773  -0.0530   0.0733   0.7790
   5.250   0.7285   0.02891   0.01852  -0.0532   0.0700   0.7803
   5.500   0.7567   0.02967   0.01928  -0.0535   0.0673   0.7814
   5.750   0.7860   0.03078   0.02032  -0.0542   0.0654   0.7822
   6.000   0.8152   0.03186   0.02159  -0.0546   0.0635   0.7829
   6.250   0.8435   0.03290   0.02284  -0.0549   0.0610   0.7837
   6.500   0.8709   0.03389   0.02395  -0.0551   0.0588   0.7845
   6.750   0.8978   0.03497   0.02510  -0.0554   0.0572   0.7852
   7.000   0.9247   0.03639   0.02655  -0.0558   0.0561   0.7860
   7.250   0.9490   0.03823   0.02876  -0.0555   0.0550   0.7868
   7.500   0.9713   0.04025   0.03121  -0.0549   0.0536   0.7880
   7.750   0.9921   0.04222   0.03353  -0.0543   0.0520   0.7891
   8.000   1.0129   0.04396   0.03551  -0.0539   0.0506   0.7902
   8.250   1.0324   0.04546   0.03718  -0.0532   0.0495   0.7909
   8.500   1.0497   0.04722   0.03910  -0.0522   0.0488   0.7915
   8.750   1.0655   0.04927   0.04132  -0.0512   0.0482   0.7921
   9.000   1.0721   0.05244   0.04493  -0.0491   0.0477   0.7927
   9.250   1.0700   0.05644   0.04949  -0.0463   0.0473   0.7933
   9.500   1.0622   0.06078   0.05433  -0.0434   0.0470   0.7939
   9.750   1.0479   0.06537   0.05936  -0.0405   0.0467   0.7945
  10.000   1.0250   0.06991   0.06426  -0.0373   0.0465   0.7951
  10.250   0.9970   0.07530   0.06996  -0.0356   0.0465   0.7956
  10.500   0.9623   0.08224   0.07718  -0.0364   0.0466   0.7961
  10.750   0.9230   0.09218   0.08737  -0.0424   0.0469   0.7964
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