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S4053 (s4053-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 500,000
Max Cl/Cd: 109.1 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4053-il-500000.txt
Download as CSV file: xf-s4053-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4053                                           
  
 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  -0.3890   0.08563   0.08340  -0.0356   1.0000   0.0171
  -8.250  -0.3911   0.08234   0.08015  -0.0365   1.0000   0.0171
  -8.000  -0.3966   0.07924   0.07710  -0.0369   1.0000   0.0171
  -7.750  -0.4091   0.07636   0.07429  -0.0366   1.0000   0.0172
  -7.500  -0.4160   0.07279   0.07076  -0.0380   1.0000   0.0172
  -7.250  -0.4242   0.06918   0.06717  -0.0388   1.0000   0.0172
  -7.000  -0.3958   0.06049   0.05834  -0.0507   0.9957   0.0173
  -6.750  -0.3834   0.05143   0.04915  -0.0593   0.9896   0.0181
  -6.500  -0.3563   0.04776   0.04538  -0.0641   0.9857   0.0188
  -6.250  -0.3293   0.04336   0.04081  -0.0686   0.9804   0.0196
  -6.000  -0.3001   0.03859   0.03580  -0.0728   0.9747   0.0214
  -5.750  -0.2600   0.03535   0.03200  -0.0760   0.9714   0.0240
  -5.500  -0.2441   0.02833   0.02469  -0.0783   0.9618   0.0259
  -5.250  -0.2122   0.02644   0.02267  -0.0805   0.9576   0.0276
  -5.000  -0.1795   0.02724   0.02319  -0.0803   0.9477   0.0328
  -4.750  -0.1584   0.02185   0.01743  -0.0814   0.9373   0.0356
  -4.500  -0.1283   0.02036   0.01581  -0.0823   0.9283   0.0380
  -4.250  -0.0988   0.01558   0.01020  -0.0805   0.9168   0.0223
  -4.000  -0.0719   0.01336   0.00763  -0.0798   0.9039   0.0205
  -3.750  -0.0452   0.01223   0.00631  -0.0792   0.8908   0.0203
  -3.500  -0.0190   0.01144   0.00537  -0.0786   0.8778   0.0205
  -3.250   0.0069   0.01091   0.00475  -0.0780   0.8653   0.0216
  -3.000   0.0328   0.01044   0.00418  -0.0774   0.8535   0.0226
  -2.750   0.0583   0.00994   0.00356  -0.0768   0.8423   0.0229
  -2.500   0.0841   0.00956   0.00308  -0.0762   0.8313   0.0236
  -2.250   0.1099   0.00914   0.00255  -0.0756   0.8207   0.0254
  -2.000   0.1363   0.00887   0.00220  -0.0751   0.8110   0.0296
  -1.750   0.1617   0.00839   0.00191  -0.0746   0.8017   0.0983
  -1.500   0.1843   0.00749   0.00179  -0.0741   0.7921   0.3335
  -1.250   0.2071   0.00688   0.00175  -0.0733   0.7836   0.5239
  -1.000   0.2283   0.00635   0.00176  -0.0719   0.7747   0.6969
  -0.750   0.2481   0.00585   0.00183  -0.0695   0.7666   0.8853
  -0.500   0.3074   0.00586   0.00182  -0.0758   0.7593   0.9755
  -0.250   0.3568   0.00589   0.00177  -0.0804   0.7510   0.9936
   0.000   0.3971   0.00594   0.00169  -0.0832   0.7428   1.0000
   0.250   0.4212   0.00597   0.00166  -0.0824   0.7331   1.0000
   0.500   0.4455   0.00603   0.00165  -0.0816   0.7242   1.0000
   0.750   0.4701   0.00610   0.00164  -0.0809   0.7156   1.0000
   1.000   0.4947   0.00615   0.00165  -0.0802   0.7065   1.0000
   1.250   0.5195   0.00623   0.00167  -0.0795   0.6977   1.0000
   1.500   0.5442   0.00630   0.00169  -0.0788   0.6881   1.0000
   1.750   0.5690   0.00637   0.00173  -0.0781   0.6781   1.0000
   2.000   0.5938   0.00645   0.00176  -0.0774   0.6683   1.0000
   2.250   0.6185   0.00654   0.00180  -0.0767   0.6579   1.0000
   2.500   0.6434   0.00661   0.00187  -0.0760   0.6469   1.0000
   2.750   0.6682   0.00669   0.00194  -0.0753   0.6355   1.0000
   3.000   0.6929   0.00679   0.00200  -0.0746   0.6227   1.0000
   3.250   0.7173   0.00689   0.00207  -0.0738   0.6081   1.0000
   3.500   0.7417   0.00700   0.00215  -0.0731   0.5920   1.0000
   3.750   0.7660   0.00713   0.00225  -0.0723   0.5747   1.0000
   4.000   0.7901   0.00728   0.00235  -0.0715   0.5552   1.0000
   4.250   0.8139   0.00746   0.00247  -0.0706   0.5312   1.0000
   4.500   0.8371   0.00768   0.00261  -0.0697   0.5028   1.0000
   4.750   0.8593   0.00798   0.00280  -0.0686   0.4667   1.0000
   5.000   0.8807   0.00837   0.00301  -0.0674   0.4254   1.0000
   5.250   0.9021   0.00879   0.00327  -0.0663   0.3845   1.0000
   5.500   0.9231   0.00927   0.00357  -0.0652   0.3419   1.0000
   5.750   0.9436   0.00981   0.00392  -0.0640   0.2962   1.0000
   6.000   0.9639   0.01038   0.00430  -0.0628   0.2523   1.0000
   6.250   0.9843   0.01095   0.00469  -0.0616   0.2133   1.0000
   6.500   1.0046   0.01153   0.00511  -0.0605   0.1774   1.0000
   6.750   1.0246   0.01214   0.00558  -0.0593   0.1441   1.0000
   7.000   1.0444   0.01275   0.00606  -0.0581   0.1152   1.0000
   7.250   1.0640   0.01339   0.00658  -0.0568   0.0931   1.0000
   7.500   1.0841   0.01397   0.00709  -0.0556   0.0763   1.0000
   7.750   1.1041   0.01454   0.00762  -0.0545   0.0639   1.0000
   8.000   1.1235   0.01515   0.00822  -0.0532   0.0553   1.0000
   8.250   1.1437   0.01566   0.00875  -0.0520   0.0491   1.0000
   8.500   1.1628   0.01626   0.00938  -0.0507   0.0438   1.0000
   8.750   1.1826   0.01677   0.00992  -0.0495   0.0391   1.0000
   9.000   1.1992   0.01751   0.01069  -0.0479   0.0343   1.0000
   9.250   1.2190   0.01797   0.01121  -0.0467   0.0299   1.0000
   9.500   1.2339   0.01879   0.01205  -0.0448   0.0249   1.0000
   9.750   1.2498   0.01947   0.01274  -0.0431   0.0209   1.0000
  10.000   1.2583   0.02049   0.01385  -0.0401   0.0182   1.0000
  10.250   1.2706   0.02125   0.01468  -0.0378   0.0165   1.0000
  10.500   1.2807   0.02216   0.01563  -0.0354   0.0148   1.0000
  10.750   1.2799   0.02384   0.01741  -0.0316   0.0136   1.0000
  11.000   1.2930   0.02460   0.01828  -0.0298   0.0128   1.0000
  11.250   1.3020   0.02568   0.01948  -0.0276   0.0120   1.0000
  11.500   1.3116   0.02672   0.02059  -0.0258   0.0112   1.0000
  11.750   1.3177   0.02807   0.02203  -0.0237   0.0107   1.0000
  12.000   1.3187   0.02992   0.02398  -0.0214   0.0102   1.0000
  12.250   1.3095   0.03293   0.02716  -0.0186   0.0096   1.0000
  12.500   1.3153   0.03461   0.02897  -0.0172   0.0094   1.0000
  12.750   1.3173   0.03676   0.03128  -0.0157   0.0093   1.0000
  13.000   1.3203   0.03885   0.03352  -0.0146   0.0090   1.0000
  13.250   1.3201   0.04140   0.03623  -0.0135   0.0088   1.0000
  13.500   1.3207   0.04389   0.03886  -0.0128   0.0086   1.0000
  13.750   1.3186   0.04683   0.04196  -0.0122   0.0084   1.0000
  14.000   1.3142   0.05015   0.04546  -0.0118   0.0083   1.0000
  14.250   1.3093   0.05362   0.04910  -0.0119   0.0081   1.0000
  14.500   1.3043   0.05723   0.05286  -0.0123   0.0079   1.0000
  14.750   1.2957   0.06150   0.05730  -0.0130   0.0078   1.0000
  15.000   1.2847   0.06637   0.06239  -0.0142   0.0079   1.0000
  15.250   1.2750   0.07127   0.06744  -0.0159   0.0078   1.0000
  15.500   1.2631   0.07680   0.07315  -0.0181   0.0076   1.0000
  15.750   1.2509   0.08274   0.07925  -0.0208   0.0076   1.0000
  16.000   1.2348   0.08973   0.08642  -0.0243   0.0076   1.0000
  16.250   1.2185   0.09714   0.09401  -0.0283   0.0076   1.0000
  16.500   1.1993   0.10564   0.10270  -0.0330   0.0077   1.0000
  16.750   1.1769   0.11531   0.11256  -0.0387   0.0077   1.0000
  17.000   1.1460   0.12766   0.12513  -0.0461   0.0080   1.0000
  17.250   1.1208   0.13939   0.13702  -0.0533   0.0081   1.0000
  17.500   1.0835   0.15540   0.15323  -0.0630   0.0085   1.0000
  17.750   0.9928   0.19261   0.19051  -0.0824   0.0097   1.0000
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