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DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DSMA-523A AIRFOIL (dsma523a-il)
Reynolds number: 500,000
Max Cl/Cd: 47.4 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dsma523a-il-500000.txt
Download as CSV file: xf-dsma523a-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.8773   0.08955   0.08638  -0.0420   1.0000   0.0295
 -14.250  -0.9328   0.07487   0.07147  -0.0519   1.0000   0.0292
 -14.000  -0.9726   0.06568   0.06203  -0.0571   1.0000   0.0291
 -13.750  -1.0058   0.05884   0.05496  -0.0596   1.0000   0.0290
 -13.500  -1.0326   0.05352   0.04942  -0.0604   1.0000   0.0290
 -13.250  -1.0548   0.04915   0.04483  -0.0601   1.0000   0.0290
 -13.000  -1.0728   0.04555   0.04101  -0.0589   1.0000   0.0291
 -12.750  -1.0872   0.04259   0.03785  -0.0572   1.0000   0.0292
 -12.500  -1.0995   0.04019   0.03525  -0.0547   1.0000   0.0293
 -12.250  -1.1126   0.03833   0.03324  -0.0512   1.0000   0.0294
 -12.000  -1.1188   0.03648   0.03122  -0.0487   1.0000   0.0295
 -11.750  -1.1180   0.03425   0.02879  -0.0473   1.0000   0.0297
 -11.500  -1.1122   0.03204   0.02645  -0.0459   1.0000   0.0300
 -11.250  -1.1007   0.03062   0.02497  -0.0449   1.0000   0.0303
 -11.000  -1.0864   0.02945   0.02374  -0.0443   1.0000   0.0306
 -10.750  -1.0699   0.02838   0.02262  -0.0439   1.0000   0.0309
 -10.500  -1.0519   0.02736   0.02153  -0.0436   1.0000   0.0313
 -10.250  -1.0331   0.02635   0.02042  -0.0432   1.0000   0.0318
 -10.000  -1.0133   0.02535   0.01933  -0.0429   1.0000   0.0323
  -9.750  -0.9927   0.02438   0.01826  -0.0426   1.0000   0.0328
  -9.500  -0.9712   0.02346   0.01723  -0.0423   1.0000   0.0334
  -9.250  -0.9487   0.02263   0.01628  -0.0420   1.0000   0.0339
  -9.000  -0.9274   0.02155   0.01517  -0.0416   1.0000   0.0346
  -8.750  -0.9030   0.02097   0.01460  -0.0417   1.0000   0.0353
  -8.500  -0.8778   0.02049   0.01410  -0.0419   1.0000   0.0360
  -8.250  -0.8525   0.01997   0.01354  -0.0421   1.0000   0.0369
  -8.000  -0.8268   0.01942   0.01293  -0.0422   1.0000   0.0379
  -7.750  -0.8009   0.01882   0.01228  -0.0424   1.0000   0.0389
  -7.500  -0.7741   0.01846   0.01194  -0.0428   1.0000   0.0399
  -7.250  -0.7468   0.01821   0.01169  -0.0432   1.0000   0.0411
  -7.000  -0.7195   0.01789   0.01133  -0.0435   1.0000   0.0425
  -6.750  -0.6921   0.01749   0.01087  -0.0438   1.0000   0.0440
  -6.500  -0.6645   0.01722   0.01064  -0.0443   1.0000   0.0453
  -6.250  -0.6366   0.01701   0.01040  -0.0447   1.0000   0.0470
  -6.000  -0.6084   0.01683   0.01014  -0.0450   1.0000   0.0489
  -5.750  -0.5805   0.01630   0.00968  -0.0455   1.0000   0.0505
  -5.500  -0.5521   0.01601   0.00940  -0.0460   1.0000   0.0526
  -5.250  -0.5238   0.01591   0.00922  -0.0463   1.0000   0.0547
  -5.000  -0.4932   0.01522   0.00865  -0.0474   1.0000   0.0574
  -4.750  -0.4637   0.01496   0.00839  -0.0481   1.0000   0.0603
  -4.500  -0.4291   0.01430   0.00780  -0.0502   1.0000   0.0635
  -4.250  -0.3965   0.01395   0.00746  -0.0516   1.0000   0.0666
  -4.000  -0.3601   0.01344   0.00702  -0.0541   1.0000   0.0704
  -3.750  -0.3266   0.01317   0.00676  -0.0557   1.0000   0.0736
  -3.500  -0.2936   0.01295   0.00658  -0.0571   1.0000   0.0769
  -3.250  -0.2611   0.01277   0.00647  -0.0584   1.0000   0.0811
  -3.000  -0.2243   0.01263   0.00643  -0.0605   0.9993   0.0901
  -2.750  -0.1864   0.01247   0.00641  -0.0630   0.9985   0.1135
  -2.500  -0.1464   0.01220   0.00637  -0.0660   0.9979   0.1571
  -2.250  -0.1033   0.01179   0.00632  -0.0699   0.9977   0.2340
  -2.000  -0.0511   0.01107   0.00614  -0.0761   0.9981   0.3671
  -1.750   0.0269   0.01034   0.00640  -0.0871   0.9948   0.6077
  -1.500   0.0879   0.01042   0.00651  -0.0933   0.9861   0.6347
  -1.250   0.1387   0.01038   0.00648  -0.0974   0.9786   0.6457
  -1.000   0.1945   0.01011   0.00618  -0.1025   0.9709   0.6562
  -0.750   0.2346   0.00989   0.00603  -0.1038   0.9599   0.6612
  -0.500   0.2497   0.00983   0.00599  -0.1004   0.9437   0.6694
  -0.250   0.2785   0.00983   0.00608  -0.0990   0.9333   0.6773
   0.000   0.3200   0.00965   0.00597  -0.1001   0.9244   0.6851
   0.250   0.3597   0.00950   0.00580  -0.1019   0.8973   0.6906
   0.500   0.4021   0.01102   0.00584  -0.1035   0.5444   0.6930
   0.750   0.4141   0.01229   0.00630  -0.1001   0.3547   0.6951
   1.000   0.4331   0.01314   0.00665  -0.0981   0.2336   0.6972
   1.250   0.4546   0.01395   0.00697  -0.0967   0.1278   0.6999
   1.500   0.4810   0.01442   0.00723  -0.0963   0.0978   0.7034
   1.750   0.5129   0.01475   0.00744  -0.0973   0.0869   0.7080
   2.000   0.5358   0.01498   0.00769  -0.0958   0.0809   0.7099
   2.250   0.5578   0.01530   0.00802  -0.0941   0.0762   0.7118
   2.500   0.5802   0.01575   0.00845  -0.0926   0.0715   0.7136
   2.750   0.6055   0.01597   0.00869  -0.0917   0.0684   0.7154
   3.000   0.6311   0.01625   0.00895  -0.0910   0.0653   0.7179
   3.250   0.6569   0.01682   0.00947  -0.0905   0.0620   0.7212
   3.500   0.6891   0.01704   0.00969  -0.0915   0.0599   0.7247
   3.750   0.7182   0.01721   0.00984  -0.0918   0.0576   0.7270
   4.000   0.7443   0.01741   0.01003  -0.0913   0.0556   0.7279
   4.250   0.7695   0.01807   0.01065  -0.0908   0.0534   0.7285
   4.500   0.7969   0.01826   0.01088  -0.0906   0.0523   0.7290
   4.750   0.8232   0.01855   0.01120  -0.0902   0.0508   0.7298
   5.000   0.8496   0.01885   0.01151  -0.0898   0.0492   0.7306
   5.250   0.8765   0.01914   0.01179  -0.0896   0.0477   0.7312
   5.500   0.9020   0.02005   0.01267  -0.0893   0.0460   0.7318
   5.750   0.9297   0.02031   0.01298  -0.0892   0.0450   0.7323
   6.000   0.9570   0.02064   0.01336  -0.0890   0.0437   0.7330
   6.250   0.9841   0.02099   0.01373  -0.0889   0.0425   0.7336
   6.500   1.0110   0.02133   0.01406  -0.0888   0.0413   0.7342
   6.750   1.0372   0.02198   0.01469  -0.0886   0.0403   0.7349
   7.000   1.0630   0.02307   0.01585  -0.0883   0.0393   0.7355
   7.250   1.0895   0.02357   0.01644  -0.0880   0.0386   0.7362
   7.500   1.1156   0.02420   0.01716  -0.0877   0.0378   0.7369
   7.750   1.1413   0.02485   0.01789  -0.0874   0.0370   0.7376
   8.000   1.1665   0.02549   0.01859  -0.0870   0.0362   0.7385
   8.250   1.1913   0.02612   0.01926  -0.0865   0.0356   0.7395
   8.500   1.2158   0.02683   0.01999  -0.0861   0.0350   0.7404
   8.750   1.2392   0.02810   0.02130  -0.0855   0.0344   0.7410
   9.000   1.2600   0.02992   0.02331  -0.0846   0.0338   0.7415
   9.250   1.2812   0.03096   0.02454  -0.0835   0.0335   0.7421
   9.500   1.3007   0.03230   0.02611  -0.0822   0.0330   0.7426
   9.750   1.3182   0.03390   0.02794  -0.0807   0.0325   0.7431
  10.000   1.3335   0.03571   0.02998  -0.0789   0.0321   0.7436
  10.250   1.3470   0.03758   0.03207  -0.0770   0.0317   0.7440
  10.500   1.3603   0.03919   0.03386  -0.0751   0.0312   0.7445
  10.750   1.3741   0.04050   0.03531  -0.0732   0.0309   0.7451
  11.000   1.3879   0.04159   0.03649  -0.0714   0.0305   0.7457
  11.250   1.3967   0.04317   0.03822  -0.0690   0.0303   0.7463
  11.500   1.4021   0.04496   0.04017  -0.0663   0.0301   0.7470
  11.750   1.4024   0.04706   0.04246  -0.0630   0.0299   0.7478
  12.000   1.3932   0.04922   0.04481  -0.0583   0.0298   0.7484
  12.250   1.3818   0.05183   0.04760  -0.0541   0.0297   0.7489
  12.500   1.3626   0.05522   0.05123  -0.0499   0.0297   0.7493
  12.750   1.3294   0.06020   0.05652  -0.0461   0.0297   0.7496
  13.000   0.8940   0.17009   0.16763  -0.1115   0.0384   0.7460
  13.250   0.8957   0.17523   0.17278  -0.1150   0.0370   0.7464
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