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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 200,000
Max Cl/Cd: 74.02 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7075-il-200000-n5.txt
Download as CSV file: xf-s7075-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7075 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3360   0.08093   0.07768  -0.0349   1.0000   0.0200
  -8.500  -0.3411   0.07852   0.07530  -0.0333   1.0000   0.0196
  -8.250  -0.4134   0.08428   0.08087  -0.0349   1.0000   0.0197
  -8.000  -0.4247   0.08238   0.07903  -0.0327   1.0000   0.0193
  -7.750  -0.4294   0.07923   0.07592  -0.0336   0.9980   0.0188
  -7.500  -0.4187   0.07357   0.07027  -0.0409   0.9921   0.0181
  -7.250  -0.4092   0.05259   0.04899  -0.0660   0.9819   0.0153
  -7.000  -0.3965   0.04589   0.04202  -0.0716   0.9757   0.0151
  -6.750  -0.3766   0.03874   0.03439  -0.0775   0.9716   0.0149
  -6.500  -0.3580   0.03335   0.02845  -0.0801   0.9667   0.0149
  -6.250  -0.3353   0.02904   0.02352  -0.0818   0.9622   0.0149
  -6.000  -0.3068   0.02577   0.01964  -0.0834   0.9594   0.0152
  -5.750  -0.2762   0.02341   0.01691  -0.0852   0.9575   0.0158
  -5.500  -0.2470   0.02242   0.01579  -0.0862   0.9547   0.0169
  -5.250  -0.2218   0.02112   0.01423  -0.0860   0.9502   0.0175
  -5.000  -0.1911   0.01963   0.01246  -0.0868   0.9473   0.0179
  -4.750  -0.1584   0.01832   0.01093  -0.0879   0.9451   0.0183
  -4.500  -0.1249   0.01719   0.00965  -0.0891   0.9432   0.0189
  -4.250  -0.0967   0.01635   0.00868  -0.0892   0.9394   0.0196
  -4.000  -0.0695   0.01566   0.00789  -0.0891   0.9347   0.0204
  -3.750  -0.0384   0.01487   0.00706  -0.0899   0.9314   0.0218
  -3.500  -0.0050   0.01432   0.00647  -0.0910   0.9289   0.0245
  -3.250   0.0226   0.01387   0.00596  -0.0910   0.9241   0.0292
  -3.000   0.0506   0.01339   0.00546  -0.0909   0.9191   0.0375
  -2.750   0.0823   0.01286   0.00501  -0.0917   0.9155   0.0619
  -2.500   0.1122   0.01229   0.00472  -0.0923   0.9114   0.1249
  -2.250   0.1371   0.01176   0.00455  -0.0920   0.9047   0.2180
  -2.000   0.1674   0.01128   0.00434  -0.0925   0.9003   0.3035
  -1.750   0.1932   0.01081   0.00423  -0.0922   0.8941   0.4121
  -1.500   0.2191   0.01034   0.00413  -0.0918   0.8879   0.5247
  -1.250   0.2455   0.00988   0.00406  -0.0911   0.8828   0.6396
  -1.000   0.2658   0.00964   0.00412  -0.0888   0.8744   0.7431
  -0.750   0.2912   0.00947   0.00403  -0.0876   0.8682   0.8085
  -0.500   0.3145   0.00938   0.00395  -0.0862   0.8591   0.8480
  -0.250   0.3397   0.00924   0.00382  -0.0850   0.8507   0.8812
   0.000   0.3689   0.00907   0.00365  -0.0847   0.8422   0.9141
   0.250   0.4069   0.00893   0.00350  -0.0865   0.8319   0.9550
   0.500   0.4444   0.00883   0.00334  -0.0884   0.8210   1.0000
   0.750   0.4717   0.00880   0.00324  -0.0881   0.8083   1.0000
   1.000   0.4988   0.00879   0.00315  -0.0877   0.7936   1.0000
   1.250   0.5261   0.00879   0.00307  -0.0874   0.7767   1.0000
   1.500   0.5537   0.00879   0.00299  -0.0871   0.7578   1.0000
   1.750   0.5812   0.00883   0.00293  -0.0868   0.7364   1.0000
   2.000   0.6084   0.00892   0.00288  -0.0864   0.7127   1.0000
   2.250   0.6347   0.00905   0.00289  -0.0859   0.6865   1.0000
   2.500   0.6606   0.00923   0.00294  -0.0853   0.6599   1.0000
   2.750   0.6860   0.00945   0.00302  -0.0847   0.6330   1.0000
   3.000   0.7109   0.00969   0.00314  -0.0840   0.6053   1.0000
   3.250   0.7353   0.00996   0.00327  -0.0832   0.5766   1.0000
   3.500   0.7594   0.01026   0.00346  -0.0825   0.5466   1.0000
   3.750   0.7831   0.01058   0.00364  -0.0816   0.5157   1.0000
   4.000   0.8064   0.01093   0.00385  -0.0808   0.4844   1.0000
   4.250   0.8295   0.01129   0.00409  -0.0799   0.4532   1.0000
   4.500   0.8523   0.01169   0.00437  -0.0790   0.4212   1.0000
   4.750   0.8748   0.01211   0.00466  -0.0781   0.3876   1.0000
   5.000   0.8969   0.01257   0.00497  -0.0772   0.3529   1.0000
   5.250   0.9188   0.01305   0.00531  -0.0762   0.3196   1.0000
   5.500   0.9408   0.01355   0.00570  -0.0753   0.2873   1.0000
   5.750   0.9625   0.01408   0.00610  -0.0744   0.2551   1.0000
   6.000   0.9837   0.01466   0.00653  -0.0734   0.2222   1.0000
   6.750   1.0466   0.01652   0.00804  -0.0706   0.1385   1.0000
   7.000   1.0673   0.01716   0.00860  -0.0696   0.1178   1.0000
   7.250   1.0876   0.01783   0.00920  -0.0686   0.0986   1.0000
   7.500   1.1075   0.01853   0.00985  -0.0675   0.0832   1.0000
   7.750   1.1274   0.01921   0.01053  -0.0664   0.0715   1.0000
   8.000   1.1469   0.01991   0.01124  -0.0652   0.0629   1.0000
   8.250   1.1650   0.02070   0.01204  -0.0638   0.0560   1.0000
   8.500   1.1837   0.02142   0.01282  -0.0625   0.0507   1.0000
   8.750   1.1994   0.02235   0.01377  -0.0609   0.0460   1.0000
   9.000   1.2169   0.02309   0.01462  -0.0594   0.0432   1.0000
   9.250   1.2323   0.02390   0.01554  -0.0577   0.0408   1.0000
   9.500   1.2459   0.02479   0.01650  -0.0557   0.0388   1.0000
   9.750   1.2572   0.02584   0.01761  -0.0534   0.0372   1.0000
  10.000   1.2659   0.02713   0.01896  -0.0510   0.0357   1.0000
  10.250   1.2789   0.02812   0.02009  -0.0491   0.0347   1.0000
  10.500   1.2910   0.02920   0.02132  -0.0472   0.0336   1.0000
  10.750   1.3025   0.03032   0.02258  -0.0453   0.0323   1.0000
  11.000   1.3132   0.03153   0.02390  -0.0435   0.0311   1.0000
  11.250   1.3230   0.03284   0.02533  -0.0417   0.0303   1.0000
  11.500   1.3318   0.03426   0.02686  -0.0399   0.0295   1.0000
  11.750   1.3396   0.03582   0.02852  -0.0381   0.0288   1.0000
  12.000   1.3462   0.03761   0.03042  -0.0364   0.0281   1.0000
  12.250   1.3518   0.03980   0.03271  -0.0348   0.0274   1.0000
  12.500   1.3585   0.04159   0.03471  -0.0333   0.0268   1.0000
  12.750   1.3640   0.04343   0.03677  -0.0319   0.0261   1.0000
  13.000   1.3679   0.04541   0.03896  -0.0307   0.0252   1.0000
  13.250   1.3707   0.04746   0.04119  -0.0296   0.0242   1.0000
  13.500   1.3724   0.04968   0.04357  -0.0288   0.0233   1.0000
  13.750   1.3734   0.05196   0.04597  -0.0284   0.0224   1.0000
  14.000   1.3729   0.05455   0.04868  -0.0282   0.0216   1.0000
  14.250   1.3702   0.05763   0.05187  -0.0282   0.0210   1.0000
  14.750   1.3595   0.06516   0.05976  -0.0293   0.0198   1.0000
  15.000   1.3532   0.06938   0.06422  -0.0305   0.0193   1.0000
  15.250   1.3454   0.07405   0.06912  -0.0322   0.0187   1.0000
  15.500   1.3366   0.07916   0.07444  -0.0344   0.0181   1.0000
  15.750   1.3263   0.08477   0.08025  -0.0371   0.0177   1.0000
  16.000   1.3136   0.09109   0.08677  -0.0403   0.0174   1.0000
  16.250   1.3003   0.09785   0.09371  -0.0440   0.0171   1.0000
  16.500   1.2849   0.10535   0.10140  -0.0483   0.0169   1.0000
  16.750   1.2659   0.11395   0.11019  -0.0534   0.0168   1.0000
  17.000   1.2410   0.12437   0.12083  -0.0598   0.0170   1.0000
  17.250   1.2035   0.13868   0.13540  -0.0688   0.0176   1.0000
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