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S3010-103-84 (s3010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 200,000
Max Cl/Cd: 68.79 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3010-il-200000-n5.txt
Download as CSV file: xf-s3010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3524   0.10382   0.10045  -0.0143   1.0000   0.0213
 -10.250  -0.4411   0.10681   0.10315  -0.0121   1.0000   0.0214
 -10.000  -0.4359   0.10336   0.09972  -0.0133   1.0000   0.0207
  -9.500  -0.4482   0.08976   0.08619  -0.0203   1.0000   0.0173
  -9.250  -0.4471   0.08573   0.08219  -0.0223   1.0000   0.0172
  -9.000  -0.4474   0.08151   0.07801  -0.0246   1.0000   0.0170
  -8.750  -0.4515   0.07641   0.07297  -0.0276   1.0000   0.0169
  -8.500  -0.4571   0.07129   0.06791  -0.0310   1.0000   0.0167
  -8.250  -0.4692   0.06504   0.06175  -0.0359   1.0000   0.0165
  -8.000  -0.4857   0.05300   0.04959  -0.0476   1.0000   0.0160
  -7.750  -0.5017   0.04351   0.03971  -0.0525   1.0000   0.0157
  -7.500  -0.5032   0.03723   0.03295  -0.0541   0.9957   0.0155
  -7.250  -0.4804   0.03135   0.02636  -0.0582   0.9797   0.0156
  -7.000  -0.4527   0.02784   0.02228  -0.0605   0.9678   0.0161
  -6.750  -0.4233   0.02521   0.01911  -0.0622   0.9570   0.0169
  -6.500  -0.3947   0.02320   0.01664  -0.0630   0.9455   0.0173
  -6.250  -0.3670   0.02155   0.01467  -0.0633   0.9338   0.0174
  -6.000  -0.3402   0.02009   0.01298  -0.0633   0.9224   0.0176
  -5.750  -0.3144   0.01883   0.01158  -0.0631   0.9111   0.0180
  -5.500  -0.2892   0.01786   0.01050  -0.0626   0.8994   0.0185
  -5.250  -0.2643   0.01704   0.00958  -0.0620   0.8875   0.0189
  -5.000  -0.2393   0.01630   0.00874  -0.0613   0.8760   0.0196
  -4.750  -0.2143   0.01563   0.00796  -0.0606   0.8649   0.0204
  -4.500  -0.1890   0.01505   0.00726  -0.0599   0.8535   0.0213
  -4.250  -0.1634   0.01450   0.00662  -0.0594   0.8419   0.0229
  -4.000  -0.1375   0.01406   0.00612  -0.0589   0.8308   0.0250
  -3.750  -0.1113   0.01364   0.00556  -0.0583   0.8200   0.0271
  -3.500  -0.0850   0.01318   0.00505  -0.0579   0.8084   0.0304
  -3.250  -0.0583   0.01275   0.00459  -0.0574   0.7971   0.0389
  -3.000  -0.0319   0.01229   0.00420  -0.0570   0.7861   0.0664
  -2.750  -0.0056   0.01186   0.00391  -0.0567   0.7749   0.1115
  -2.500   0.0209   0.01146   0.00371  -0.0565   0.7631   0.1685
  -2.250   0.0471   0.01103   0.00354  -0.0563   0.7516   0.2453
  -2.000   0.0735   0.01069   0.00338  -0.0560   0.7402   0.3161
  -1.750   0.1000   0.01041   0.00325  -0.0557   0.7285   0.3810
  -1.500   0.1263   0.01013   0.00317  -0.0553   0.7163   0.4559
  -1.250   0.1523   0.00987   0.00310  -0.0547   0.7042   0.5296
  -1.000   0.1780   0.00967   0.00305  -0.0540   0.6922   0.5990
  -0.750   0.2031   0.00949   0.00301  -0.0531   0.6800   0.6665
  -0.500   0.2275   0.00933   0.00299  -0.0519   0.6674   0.7329
  -0.250   0.2514   0.00920   0.00297  -0.0505   0.6544   0.7968
   0.000   0.2764   0.00911   0.00294  -0.0492   0.6415   0.8590
   0.250   0.3080   0.00906   0.00287  -0.0494   0.6280   0.9217
   0.500   0.3494   0.00905   0.00276  -0.0520   0.6135   0.9809
   0.750   0.3805   0.00914   0.00271  -0.0526   0.5995   1.0000
   1.000   0.4071   0.00926   0.00270  -0.0523   0.5860   1.0000
   1.250   0.4339   0.00938   0.00271  -0.0520   0.5725   1.0000
   1.500   0.4607   0.00952   0.00273  -0.0517   0.5585   1.0000
   1.750   0.4876   0.00966   0.00277  -0.0515   0.5443   1.0000
   2.000   0.5145   0.00981   0.00283  -0.0512   0.5299   1.0000
   2.250   0.5414   0.00996   0.00290  -0.0510   0.5156   1.0000
   2.500   0.5683   0.01013   0.00298  -0.0507   0.5016   1.0000
   2.750   0.5952   0.01030   0.00308  -0.0505   0.4878   1.0000
   3.000   0.6221   0.01048   0.00320  -0.0503   0.4738   1.0000
   3.250   0.6489   0.01068   0.00333  -0.0501   0.4600   1.0000
   3.500   0.6756   0.01088   0.00347  -0.0498   0.4458   1.0000
   3.750   0.7022   0.01109   0.00363  -0.0496   0.4316   1.0000
   4.000   0.7287   0.01132   0.00381  -0.0493   0.4171   1.0000
   4.250   0.7551   0.01156   0.00399  -0.0491   0.4023   1.0000
   4.500   0.7813   0.01180   0.00419  -0.0488   0.3872   1.0000
   4.750   0.8075   0.01206   0.00443  -0.0486   0.3723   1.0000
   5.000   0.8335   0.01234   0.00466  -0.0483   0.3571   1.0000
   5.250   0.8593   0.01263   0.00491  -0.0480   0.3416   1.0000
   5.500   0.8850   0.01293   0.00518  -0.0477   0.3261   1.0000
   5.750   0.9104   0.01326   0.00549  -0.0474   0.3105   1.0000
   6.000   0.9356   0.01360   0.00580  -0.0471   0.2947   1.0000
   6.250   0.9606   0.01397   0.00614  -0.0467   0.2791   1.0000
   6.500   0.9853   0.01436   0.00652  -0.0463   0.2636   1.0000
   6.750   1.0097   0.01477   0.00690  -0.0459   0.2487   1.0000
   7.000   1.0338   0.01520   0.00732  -0.0455   0.2341   1.0000
   7.250   1.0577   0.01565   0.00776  -0.0450   0.2197   1.0000
   7.500   1.0811   0.01613   0.00824  -0.0445   0.2054   1.0000
   7.750   1.1042   0.01663   0.00873  -0.0440   0.1921   1.0000
   8.000   1.1269   0.01717   0.00925  -0.0434   0.1789   1.0000
   8.250   1.1492   0.01772   0.00982  -0.0428   0.1665   1.0000
   8.500   1.1708   0.01831   0.01041  -0.0421   0.1543   1.0000
   8.750   1.1918   0.01895   0.01104  -0.0414   0.1429   1.0000
   9.000   1.2127   0.01956   0.01168  -0.0407   0.1321   1.0000
   9.250   1.2330   0.02021   0.01237  -0.0399   0.1223   1.0000
   9.500   1.2521   0.02093   0.01312  -0.0389   0.1135   1.0000
   9.750   1.2702   0.02169   0.01390  -0.0379   0.1051   1.0000
  10.000   1.2884   0.02242   0.01471  -0.0369   0.0979   1.0000
  10.250   1.3035   0.02332   0.01561  -0.0355   0.0912   1.0000
  10.500   1.3198   0.02409   0.01650  -0.0343   0.0845   1.0000
  10.750   1.3313   0.02508   0.01751  -0.0326   0.0787   1.0000
  11.000   1.3431   0.02594   0.01846  -0.0309   0.0727   1.0000
  11.250   1.3503   0.02710   0.01963  -0.0289   0.0675   1.0000
  11.500   1.3606   0.02813   0.02076  -0.0273   0.0617   1.0000
  11.750   1.3663   0.02952   0.02216  -0.0257   0.0567   1.0000
  12.000   1.3750   0.03079   0.02354  -0.0245   0.0518   1.0000
  12.250   1.3794   0.03245   0.02526  -0.0232   0.0483   1.0000
  12.500   1.3855   0.03408   0.02700  -0.0222   0.0451   1.0000
  12.750   1.3902   0.03591   0.02893  -0.0214   0.0418   1.0000
  13.000   1.3910   0.03821   0.03129  -0.0208   0.0391   1.0000
  13.250   1.3951   0.04031   0.03353  -0.0204   0.0365   1.0000
  13.500   1.3965   0.04278   0.03612  -0.0203   0.0339   1.0000
  13.750   1.3942   0.04578   0.03920  -0.0204   0.0319   1.0000
  14.000   1.3938   0.04871   0.04228  -0.0207   0.0299   1.0000
  14.250   1.3915   0.05199   0.04570  -0.0213   0.0279   1.0000
  14.500   1.3859   0.05583   0.04965  -0.0222   0.0261   1.0000
  14.750   1.3785   0.06008   0.05402  -0.0235   0.0248   1.0000
  15.000   1.3727   0.06427   0.05837  -0.0249   0.0234   1.0000
  15.250   1.3643   0.06901   0.06326  -0.0267   0.0220   1.0000
  15.500   1.3537   0.07430   0.06867  -0.0289   0.0210   1.0000
  15.750   1.3412   0.08012   0.07461  -0.0316   0.0203   1.0000
  16.000   1.3289   0.08611   0.08075  -0.0343   0.0195   1.0000
  16.250   1.3172   0.09221   0.08700  -0.0373   0.0187   1.0000
  16.500   1.3046   0.09862   0.09357  -0.0404   0.0181   1.0000
  16.750   1.2911   0.10538   0.10047  -0.0439   0.0176   1.0000
  17.000   1.2776   0.11233   0.10756  -0.0475   0.0172   1.0000
  17.250   1.2635   0.11958   0.11495  -0.0515   0.0168   1.0000
  17.500   1.2501   0.12679   0.12228  -0.0554   0.0166   1.0000
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