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S8064 (s8064-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S8064 (s8064-il)
Reynolds number: 500,000
Max Cl/Cd: 80.17 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8064-il-500000.txt
Download as CSV file: xf-s8064-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8064                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5213   0.08451   0.08238  -0.0535   1.0000   0.0241
 -11.000  -0.5490   0.07209   0.06996  -0.0630   1.0000   0.0234
 -10.750  -0.5777   0.06344   0.06117  -0.0707   0.9927   0.0231
 -10.500  -0.6843   0.04082   0.03735  -0.0789   0.9748   0.0137
 -10.250  -0.6934   0.03711   0.03336  -0.0772   0.9669   0.0131
 -10.000  -0.7289   0.02928   0.02457  -0.0707   0.9574   0.0111
  -9.750  -0.7212   0.02692   0.02181  -0.0683   0.9531   0.0107
  -9.500  -0.7081   0.02532   0.01996  -0.0666   0.9493   0.0106
  -9.250  -0.6936   0.02355   0.01797  -0.0650   0.9462   0.0106
  -9.000  -0.6783   0.02172   0.01594  -0.0635   0.9436   0.0108
  -8.750  -0.6603   0.02043   0.01453  -0.0624   0.9407   0.0110
  -8.500  -0.6419   0.01945   0.01347  -0.0613   0.9378   0.0115
  -8.250  -0.6233   0.01856   0.01249  -0.0600   0.9350   0.0117
  -8.000  -0.6045   0.01781   0.01163  -0.0587   0.9324   0.0123
  -7.750  -0.5864   0.01710   0.01083  -0.0572   0.9300   0.0126
  -7.500  -0.5654   0.01646   0.01011  -0.0563   0.9275   0.0133
  -7.250  -0.5452   0.01584   0.00941  -0.0552   0.9247   0.0138
  -7.000  -0.5263   0.01515   0.00864  -0.0539   0.9219   0.0145
  -6.750  -0.5075   0.01454   0.00801  -0.0525   0.9192   0.0166
  -6.500  -0.4866   0.01413   0.00753  -0.0513   0.9169   0.0184
  -6.250  -0.4666   0.01352   0.00688  -0.0500   0.9144   0.0223
  -6.000  -0.4463   0.01289   0.00632  -0.0489   0.9113   0.0382
  -5.750  -0.4239   0.01252   0.00600  -0.0481   0.9084   0.0544
  -5.500  -0.4012   0.01220   0.00572  -0.0473   0.9059   0.0705
  -5.250  -0.3791   0.01185   0.00545  -0.0464   0.9036   0.0936
  -5.000  -0.3577   0.01148   0.00523  -0.0454   0.9013   0.1286
  -4.750  -0.3361   0.01100   0.00500  -0.0447   0.8979   0.1824
  -4.500  -0.3162   0.01043   0.00475  -0.0436   0.8946   0.2558
  -4.250  -0.2966   0.00987   0.00449  -0.0424   0.8916   0.3394
  -4.000  -0.2770   0.00935   0.00429  -0.0410   0.8891   0.4244
  -3.750  -0.2562   0.00900   0.00418  -0.0398   0.8864   0.4973
  -3.500  -0.2340   0.00872   0.00410  -0.0388   0.8825   0.5558
  -3.250  -0.2109   0.00848   0.00401  -0.0379   0.8792   0.6053
  -3.000  -0.1868   0.00830   0.00395  -0.0370   0.8765   0.6459
  -2.750  -0.1617   0.00821   0.00393  -0.0363   0.8742   0.6808
  -2.500  -0.1361   0.00822   0.00395  -0.0358   0.8712   0.7070
  -2.250  -0.1101   0.00822   0.00397  -0.0354   0.8672   0.7259
  -2.000  -0.0836   0.00820   0.00394  -0.0350   0.8639   0.7423
  -1.750  -0.0566   0.00817   0.00390  -0.0346   0.8613   0.7561
  -1.500  -0.0296   0.00816   0.00386  -0.0342   0.8590   0.7686
  -1.250  -0.0036   0.00819   0.00390  -0.0339   0.8546   0.7808
  -1.000   0.0231   0.00818   0.00390  -0.0335   0.8506   0.7917
  -0.750   0.0503   0.00813   0.00386  -0.0332   0.8476   0.8013
  -0.500   0.0778   0.00809   0.00379  -0.0329   0.8450   0.8106
  -0.250   0.1044   0.00808   0.00382  -0.0326   0.8404   0.8180
   0.000   0.1314   0.00804   0.00377  -0.0324   0.8358   0.8253
   0.250   0.1593   0.00794   0.00369  -0.0322   0.8324   0.8312
   0.500   0.1874   0.00788   0.00360  -0.0321   0.8291   0.8378
   0.750   0.2138   0.00781   0.00358  -0.0318   0.8227   0.8432
   1.000   0.2417   0.00770   0.00347  -0.0317   0.8181   0.8489
   1.250   0.2693   0.00760   0.00337  -0.0315   0.8129   0.8546
   1.500   0.2963   0.00749   0.00330  -0.0312   0.8058   0.8594
   1.750   0.3245   0.00736   0.00316  -0.0311   0.8002   0.8649
   2.000   0.3509   0.00725   0.00309  -0.0308   0.7910   0.8701
   2.250   0.3780   0.00713   0.00301  -0.0305   0.7821   0.8750
   2.500   0.4052   0.00701   0.00289  -0.0302   0.7720   0.8805
   2.750   0.4318   0.00691   0.00282  -0.0298   0.7589   0.8855
   3.000   0.4579   0.00685   0.00277  -0.0294   0.7422   0.8908
   3.250   0.4836   0.00684   0.00273  -0.0288   0.7224   0.8968
   3.500   0.5090   0.00687   0.00272  -0.0282   0.7011   0.9020
   3.750   0.5336   0.00695   0.00277  -0.0275   0.6777   0.9085
   4.000   0.5575   0.00707   0.00284  -0.0267   0.6502   0.9150
   4.250   0.5800   0.00725   0.00294  -0.0256   0.6180   0.9224
   4.500   0.6013   0.00750   0.00308  -0.0243   0.5770   0.9306
   4.750   0.6203   0.00785   0.00327  -0.0226   0.5270   0.9406
   5.000   0.6409   0.00837   0.00355  -0.0214   0.4598   0.9497
   5.250   0.6622   0.00908   0.00392  -0.0207   0.3805   0.9598
   5.500   0.6858   0.00991   0.00438  -0.0207   0.2977   0.9698
   5.750   0.7147   0.01081   0.00490  -0.0220   0.2168   0.9763
   6.000   0.7429   0.01166   0.00542  -0.0231   0.1516   0.9841
   6.250   0.7753   0.01242   0.00595  -0.0249   0.1058   0.9892
   6.500   0.8077   0.01308   0.00648  -0.0267   0.0799   0.9953
   6.750   0.8419   0.01367   0.00698  -0.0289   0.0634   1.0000
   7.000   0.8434   0.01395   0.00722  -0.0242   0.0576   1.0000
   7.250   0.8564   0.01425   0.00753  -0.0216   0.0521   1.0000
   7.500   0.8679   0.01474   0.00799  -0.0188   0.0462   1.0000
   7.750   0.8825   0.01504   0.00835  -0.0165   0.0424   1.0000
   8.000   0.8937   0.01559   0.00886  -0.0138   0.0373   1.0000
   8.250   0.9094   0.01597   0.00929  -0.0118   0.0335   1.0000
   8.500   0.9219   0.01662   0.00992  -0.0094   0.0284   1.0000
   8.750   0.9378   0.01712   0.01046  -0.0077   0.0244   1.0000
   9.000   0.9483   0.01801   0.01134  -0.0052   0.0208   1.0000
   9.250   0.9628   0.01868   0.01208  -0.0033   0.0190   1.0000
   9.500   0.9776   0.01935   0.01281  -0.0016   0.0174   1.0000
   9.750   0.9914   0.02011   0.01361   0.0002   0.0165   1.0000
  10.000   0.9966   0.02158   0.01514   0.0031   0.0152   1.0000
  10.250   1.0092   0.02255   0.01620   0.0049   0.0147   1.0000
  10.500   1.0221   0.02353   0.01728   0.0067   0.0143   1.0000
  10.750   1.0347   0.02458   0.01843   0.0084   0.0138   1.0000
  11.000   1.0471   0.02564   0.01958   0.0100   0.0131   1.0000
  11.250   1.0606   0.02644   0.02043   0.0114   0.0124   1.0000
  11.500   1.0710   0.02761   0.02168   0.0130   0.0118   1.0000
  11.750   1.0802   0.02898   0.02314   0.0147   0.0115   1.0000
  12.000   1.0823   0.03175   0.02609   0.0170   0.0110   1.0000
  12.250   1.0896   0.03351   0.02801   0.0187   0.0108   1.0000
  12.500   1.0961   0.03515   0.02982   0.0203   0.0107   1.0000
  12.750   1.1007   0.03693   0.03178   0.0220   0.0105   1.0000
  13.000   1.1027   0.03909   0.03413   0.0236   0.0103   1.0000
  13.250   1.1019   0.04155   0.03678   0.0252   0.0103   1.0000
  13.500   1.0981   0.04429   0.03973   0.0266   0.0101   1.0000
  13.750   1.0929   0.04719   0.04284   0.0278   0.0100   1.0000
  14.000   1.0826   0.05084   0.04670   0.0286   0.0100   1.0000
  14.250   1.0712   0.05472   0.05079   0.0289   0.0100   1.0000
  14.500   1.0588   0.05890   0.05516   0.0285   0.0098   1.0000
  14.750   1.0407   0.06425   0.06073   0.0274   0.0099   1.0000
  15.000   1.0215   0.07024   0.06693   0.0253   0.0099   1.0000
  15.250   0.9999   0.07722   0.07411   0.0221   0.0099   1.0000
  15.500   0.9747   0.08562   0.08271   0.0175   0.0101   1.0000
  15.750   0.9551   0.09381   0.09107   0.0124   0.0099   1.0000
  16.000   0.9242   0.10519   0.10261   0.0054   0.0104   1.0000
  16.250   0.8921   0.11814   0.11572  -0.0026   0.0105   1.0000
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