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S2055 (s2055-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S2055 (s2055-il)
Reynolds number: 500,000
Max Cl/Cd: 92.85 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2055-il-500000.txt
Download as CSV file: xf-s2055-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2055                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4931   0.07598   0.07381  -0.0349   1.0000   0.0153
  -8.250  -0.5013   0.07191   0.06977  -0.0380   1.0000   0.0152
  -8.000  -0.5082   0.06797   0.06581  -0.0393   1.0000   0.0151
  -7.750  -0.5277   0.06224   0.06004  -0.0397   1.0000   0.0155
  -7.500  -0.5353   0.05831   0.05604  -0.0389   1.0000   0.0156
  -7.250  -0.5397   0.05560   0.05329  -0.0371   1.0000   0.0159
  -7.000  -0.5420   0.05240   0.05001  -0.0355   1.0000   0.0161
  -6.750  -0.5414   0.04994   0.04748  -0.0336   1.0000   0.0165
  -6.500  -0.5389   0.04763   0.04509  -0.0317   1.0000   0.0171
  -6.250  -0.5198   0.04354   0.04080  -0.0335   0.9981   0.0180
  -6.000  -0.4898   0.03890   0.03585  -0.0365   0.9952   0.0206
  -5.750  -0.4542   0.03718   0.03371  -0.0378   0.9925   0.0223
  -5.500  -0.4381   0.02839   0.02435  -0.0401   0.9879   0.0240
  -5.250  -0.4074   0.02592   0.02171  -0.0418   0.9855   0.0250
  -5.000  -0.3775   0.01770   0.01237  -0.0406   0.9837   0.0134
  -4.750  -0.3479   0.01569   0.01004  -0.0408   0.9806   0.0137
  -4.500  -0.3167   0.01443   0.00857  -0.0414   0.9772   0.0144
  -4.250  -0.2848   0.01286   0.00680  -0.0423   0.9747   0.0158
  -4.000  -0.2505   0.01204   0.00597  -0.0439   0.9727   0.0189
  -3.750  -0.2142   0.01145   0.00531  -0.0457   0.9711   0.0218
  -3.500  -0.1842   0.01051   0.00428  -0.0462   0.9672   0.0264
  -3.250  -0.1516   0.01020   0.00395  -0.0472   0.9633   0.0322
  -3.000  -0.1166   0.00957   0.00336  -0.0488   0.9608   0.0507
  -2.750  -0.0816   0.00900   0.00303  -0.0505   0.9586   0.1102
  -2.500  -0.0474   0.00840   0.00277  -0.0522   0.9565   0.2052
  -2.250  -0.0240   0.00768   0.00258  -0.0517   0.9488   0.3552
  -2.000   0.0033   0.00675   0.00238  -0.0519   0.9444   0.5641
  -1.750   0.0238   0.00606   0.00236  -0.0501   0.9369   0.7515
  -1.500   0.0496   0.00583   0.00231  -0.0490   0.9304   0.8296
  -1.250   0.0737   0.00572   0.00224  -0.0476   0.9209   0.8629
  -1.000   0.0988   0.00563   0.00214  -0.0464   0.9112   0.8877
  -0.750   0.1238   0.00556   0.00204  -0.0452   0.9003   0.9050
  -0.500   0.1473   0.00553   0.00197  -0.0437   0.8879   0.9235
  -0.250   0.1701   0.00555   0.00196  -0.0419   0.8759   0.9435
   0.000   0.1979   0.00558   0.00195  -0.0414   0.8651   0.9579
   0.250   0.2321   0.00562   0.00194  -0.0424   0.8549   0.9683
   0.500   0.2725   0.00566   0.00191  -0.0449   0.8450   0.9741
   0.750   0.3133   0.00569   0.00190  -0.0476   0.8333   0.9789
   1.000   0.3516   0.00573   0.00188  -0.0498   0.8202   0.9841
   1.250   0.3921   0.00575   0.00186  -0.0525   0.8064   0.9877
   1.500   0.4292   0.00579   0.00184  -0.0545   0.7907   0.9922
   1.750   0.4657   0.00582   0.00183  -0.0564   0.7738   0.9960
   2.000   0.5025   0.00585   0.00182  -0.0584   0.7527   0.9997
   2.250   0.5253   0.00590   0.00181  -0.0574   0.7309   1.0000
   2.500   0.5462   0.00598   0.00182  -0.0560   0.7044   1.0000
   2.750   0.5664   0.00610   0.00184  -0.0544   0.6708   1.0000
   3.000   0.5845   0.00633   0.00187  -0.0524   0.6180   1.0000
   3.250   0.5994   0.00677   0.00197  -0.0499   0.5359   1.0000
   3.500   0.6144   0.00730   0.00214  -0.0475   0.4551   1.0000
   3.750   0.6317   0.00776   0.00234  -0.0456   0.3941   1.0000
   4.000   0.6511   0.00814   0.00255  -0.0441   0.3495   1.0000
   4.250   0.6715   0.00852   0.00276  -0.0428   0.3110   1.0000
   4.500   0.6928   0.00889   0.00301  -0.0416   0.2751   1.0000
   4.750   0.7149   0.00927   0.00325  -0.0407   0.2428   1.0000
   5.000   0.7378   0.00963   0.00350  -0.0399   0.2123   1.0000
   5.250   0.7611   0.00998   0.00377  -0.0392   0.1863   1.0000
   5.500   0.7843   0.01038   0.00407  -0.0385   0.1538   1.0000
   5.750   0.8058   0.01100   0.00444  -0.0376   0.1059   1.0000
   6.000   0.8269   0.01169   0.00493  -0.0366   0.0695   1.0000
   6.250   0.8491   0.01229   0.00546  -0.0357   0.0497   1.0000
   6.500   0.8710   0.01298   0.00610  -0.0348   0.0366   1.0000
   6.750   0.8931   0.01363   0.00683  -0.0338   0.0301   1.0000
   7.000   0.9155   0.01424   0.00747  -0.0329   0.0261   1.0000
   7.250   0.9340   0.01535   0.00868  -0.0314   0.0230   1.0000
   7.500   0.9574   0.01581   0.00921  -0.0307   0.0210   1.0000
   7.750   0.9791   0.01648   0.00995  -0.0297   0.0192   1.0000
   8.000   0.9989   0.01737   0.01089  -0.0286   0.0171   1.0000
   8.250   1.0152   0.01884   0.01251  -0.0269   0.0153   1.0000
   8.500   1.0364   0.01960   0.01339  -0.0259   0.0141   1.0000
   8.750   1.0565   0.02047   0.01436  -0.0248   0.0128   1.0000
   9.000   1.0755   0.02141   0.01537  -0.0236   0.0117   1.0000
   9.250   1.0852   0.02441   0.01860  -0.0212   0.0105   1.0000
   9.500   1.0998   0.02647   0.02092  -0.0195   0.0101   1.0000
   9.750   1.1169   0.02756   0.02220  -0.0181   0.0095   1.0000
  10.000   1.1322   0.02880   0.02361  -0.0165   0.0089   1.0000
  10.250   1.1459   0.03002   0.02498  -0.0149   0.0082   1.0000
  10.500   1.1557   0.03171   0.02686  -0.0129   0.0079   1.0000
  10.750   1.1649   0.03292   0.02821  -0.0108   0.0075   1.0000
  11.000   1.1643   0.03512   0.03064  -0.0075   0.0074   1.0000
  11.250   1.1620   0.03713   0.03283  -0.0044   0.0072   1.0000
  11.500   1.1555   0.03955   0.03544  -0.0014   0.0071   1.0000
  11.750   1.1435   0.04262   0.03873   0.0014   0.0070   1.0000
  12.000   1.1297   0.04604   0.04238   0.0033   0.0069   1.0000
  12.250   1.1097   0.05045   0.04702   0.0042   0.0068   1.0000
  12.500   1.1002   0.05410   0.05089   0.0040   0.0071   1.0000
  12.750   1.0750   0.06025   0.05722   0.0020   0.0068   1.0000
  13.000   1.0594   0.06601   0.06316  -0.0011   0.0069   1.0000
  13.250   1.0421   0.07302   0.07034  -0.0057   0.0069   1.0000
  13.500   1.0241   0.08138   0.07887  -0.0116   0.0069   1.0000
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