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S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il)
Reynolds number: 1,000,000
Max Cl/Cd: 82.81 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4094-il-1000000-n5.txt
Download as CSV file: xf-s4094-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4094 (root airfoil designed for and used on the
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6430   0.13110   0.12952   0.0335   1.0004   0.0063
 -10.750  -0.6436   0.12572   0.12415   0.0312   1.0004   0.0064
 -10.250  -0.9063   0.03910   0.03673  -0.0243   1.0004   0.0073
 -10.000  -0.8923   0.03420   0.03142  -0.0264   1.0004   0.0074
  -9.750  -0.8717   0.03125   0.02816  -0.0276   1.0004   0.0074
  -9.500  -0.8486   0.02891   0.02555  -0.0285   1.0004   0.0075
  -9.250  -0.8238   0.02705   0.02345  -0.0292   1.0004   0.0075
  -9.000  -0.7992   0.02449   0.02058  -0.0302   1.0004   0.0076
  -8.750  -0.7736   0.02196   0.01772  -0.0311   1.0004   0.0078
  -8.500  -0.7461   0.02056   0.01615  -0.0317   1.0004   0.0079
  -8.250  -0.7181   0.01953   0.01499  -0.0322   1.0004   0.0081
  -8.000  -0.6897   0.01869   0.01403  -0.0327   1.0004   0.0082
  -7.750  -0.6610   0.01793   0.01318  -0.0332   1.0004   0.0083
  -7.500  -0.6322   0.01732   0.01251  -0.0337   1.0004   0.0085
  -7.250  -0.6032   0.01673   0.01185  -0.0341   1.0004   0.0087
  -7.000  -0.5740   0.01611   0.01116  -0.0346   1.0004   0.0090
  -6.750  -0.5447   0.01543   0.01039  -0.0350   1.0004   0.0092
  -6.500  -0.5153   0.01479   0.00967  -0.0355   1.0004   0.0094
  -6.250  -0.4850   0.01431   0.00912  -0.0361   0.9695   0.0097
  -6.000  -0.4611   0.01411   0.00874  -0.0350   0.9098   0.0099
  -5.750  -0.4348   0.01384   0.00828  -0.0345   0.8699   0.0101
  -5.500  -0.4066   0.01355   0.00781  -0.0345   0.8374   0.0103
  -5.250  -0.3779   0.01328   0.00739  -0.0347   0.8084   0.0105
  -5.000  -0.3487   0.01302   0.00699  -0.0349   0.7827   0.0106
  -4.750  -0.3194   0.01277   0.00662  -0.0352   0.7599   0.0108
  -4.500  -0.2898   0.01246   0.00618  -0.0356   0.7386   0.0109
  -4.250  -0.2600   0.01207   0.00567  -0.0360   0.7193   0.0113
  -4.000  -0.2303   0.01179   0.00529  -0.0364   0.7014   0.0117
  -3.750  -0.2006   0.01158   0.00500  -0.0368   0.6849   0.0122
  -3.500  -0.1709   0.01142   0.00477  -0.0372   0.6690   0.0128
  -3.250  -0.1411   0.01127   0.00455  -0.0375   0.6541   0.0135
  -3.000  -0.1114   0.01113   0.00434  -0.0379   0.6403   0.0140
  -2.750  -0.0816   0.01103   0.00417  -0.0383   0.6270   0.0146
  -2.500  -0.0519   0.01093   0.00401  -0.0386   0.6141   0.0152
  -2.250  -0.0221   0.01083   0.00385  -0.0390   0.6017   0.0168
  -2.000   0.0076   0.01073   0.00372  -0.0393   0.5897   0.0196
  -1.750   0.0375   0.01054   0.00359  -0.0398   0.5780   0.0439
  -1.500   0.0674   0.01038   0.00350  -0.0403   0.5669   0.0718
  -1.250   0.0972   0.01023   0.00343  -0.0407   0.5559   0.1054
  -1.000   0.1270   0.01010   0.00337  -0.0412   0.5441   0.1425
  -0.750   0.1569   0.00994   0.00333  -0.0417   0.5326   0.1890
  -0.500   0.1867   0.00982   0.00330  -0.0422   0.5208   0.2340
  -0.250   0.2166   0.00969   0.00328  -0.0427   0.5083   0.2866
   0.000   0.2465   0.00943   0.00329  -0.0434   0.4950   0.3906
   0.250   0.2764   0.00921   0.00331  -0.0440   0.4806   0.4893
   0.500   0.3061   0.00907   0.00334  -0.0446   0.4659   0.5675
   0.750   0.3358   0.00891   0.00338  -0.0451   0.4508   0.6523
   1.000   0.3648   0.00867   0.00346  -0.0454   0.4341   0.7733
   1.250   0.3885   0.00834   0.00349  -0.0442   0.4188   0.9112
   1.500   0.4150   0.00802   0.00319  -0.0437   0.4033   0.9996
   1.750   0.4447   0.00816   0.00323  -0.0441   0.3873   0.9996
   2.000   0.4743   0.00831   0.00329  -0.0445   0.3705   0.9996
   2.250   0.5039   0.00845   0.00336  -0.0449   0.3549   0.9996
   2.500   0.5334   0.00860   0.00343  -0.0453   0.3398   0.9996
   3.000   0.5924   0.00893   0.00360  -0.0461   0.3095   0.9996
   3.250   0.6218   0.00910   0.00370  -0.0465   0.2942   0.9996
   3.500   0.6512   0.00927   0.00381  -0.0469   0.2805   0.9996
   3.750   0.6805   0.00946   0.00393  -0.0473   0.2658   0.9996
   4.000   0.7098   0.00965   0.00405  -0.0477   0.2517   0.9996
   4.250   0.7390   0.00985   0.00420  -0.0481   0.2371   0.9996
   4.500   0.7682   0.01006   0.00434  -0.0485   0.2236   0.9996
   4.750   0.7973   0.01028   0.00450  -0.0489   0.2094   0.9996
   5.000   0.8264   0.01049   0.00466  -0.0493   0.1973   0.9996
   5.250   0.8555   0.01070   0.00484  -0.0496   0.1862   0.9996
   5.500   0.8844   0.01094   0.00503  -0.0500   0.1734   0.9996
   5.750   0.9133   0.01117   0.00523  -0.0504   0.1629   0.9996
   6.000   0.9420   0.01144   0.00544  -0.0508   0.1512   0.9996
   6.250   0.9707   0.01173   0.00568  -0.0511   0.1385   0.9996
   6.500   0.9991   0.01207   0.00594  -0.0515   0.1224   0.9996
   6.750   1.0275   0.01241   0.00622  -0.0519   0.1085   0.9996
   7.000   1.0558   0.01275   0.00650  -0.0522   0.0971   0.9996
   7.250   1.0840   0.01311   0.00682  -0.0525   0.0859   0.9996
   7.500   1.1120   0.01349   0.00714  -0.0529   0.0757   0.9996
   7.750   1.1399   0.01387   0.00749  -0.0532   0.0660   0.9996
   8.000   1.1677   0.01428   0.00785  -0.0535   0.0562   0.9996
   8.250   1.1953   0.01470   0.00824  -0.0537   0.0479   0.9996
   8.500   1.2225   0.01517   0.00867  -0.0540   0.0394   0.9996
   8.750   1.2496   0.01566   0.00912  -0.0542   0.0320   0.9996
   9.000   1.2764   0.01617   0.00960  -0.0544   0.0256   0.9996
   9.250   1.3028   0.01674   0.01015  -0.0546   0.0193   0.9996
   9.500   1.3280   0.01760   0.01093  -0.0547   0.0084   0.9996
   9.750   1.3536   0.01825   0.01159  -0.0547   0.0058   0.9996
  10.000   1.3795   0.01877   0.01216  -0.0547   0.0050   0.9996
  10.250   1.4049   0.01935   0.01278  -0.0547   0.0045   0.9996
  10.500   1.4299   0.01997   0.01346  -0.0547   0.0040   0.9996
  10.750   1.4543   0.02064   0.01420  -0.0545   0.0037   0.9996
  11.000   1.4787   0.02123   0.01485  -0.0544   0.0036   0.9996
  11.250   1.5025   0.02187   0.01555  -0.0542   0.0035   0.9996
  11.500   1.5257   0.02255   0.01630  -0.0539   0.0033   0.9996
  11.750   1.5480   0.02328   0.01710  -0.0535   0.0032   0.9996
  12.000   1.5695   0.02406   0.01798  -0.0530   0.0031   0.9996
  12.250   1.5900   0.02490   0.01889  -0.0524   0.0030   0.9996
  12.500   1.6094   0.02579   0.01986  -0.0517   0.0029   0.9996
  12.750   1.6273   0.02675   0.02091  -0.0507   0.0028   0.9996
  13.000   1.6435   0.02780   0.02205  -0.0496   0.0027   0.9996
  13.250   1.6573   0.02897   0.02331  -0.0482   0.0026   0.9996
  13.500   1.6681   0.03028   0.02472  -0.0465   0.0026   0.9996
  13.750   1.6749   0.03178   0.02633  -0.0443   0.0025   0.9996
  14.000   1.6711   0.03365   0.02833  -0.0408   0.0024   0.9996
  14.250   1.6639   0.03613   0.03094  -0.0380   0.0024   0.9996
  14.500   1.6580   0.03921   0.03417  -0.0368   0.0024   0.9996
  14.750   1.6511   0.04300   0.03811  -0.0368   0.0023   0.9996
  15.000   1.6415   0.04756   0.04283  -0.0376   0.0023   0.9996
  15.250   1.6303   0.05269   0.04811  -0.0390   0.0023   0.9996
  15.500   1.6157   0.05853   0.05411  -0.0410   0.0022   0.9996
  15.750   1.5995   0.06470   0.06043  -0.0431   0.0022   0.9996
  16.000   1.5823   0.07116   0.06704  -0.0455   0.0022   0.9996
  16.250   1.5610   0.07840   0.07444  -0.0482   0.0022   0.9996
  16.500   1.5368   0.08627   0.08246  -0.0513   0.0022   0.9996
  16.750   1.5107   0.09473   0.09107  -0.0547   0.0022   0.9996
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