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S4158 (s4158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4158 (s4158-il)
Reynolds number: 1,000,000
Max Cl/Cd: 150.61 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4158-il-1000000.txt
Download as CSV file: xf-s4158-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4158                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3215   0.09636   0.09411  -0.0458   0.8299   0.0119
  -9.750  -0.3194   0.09210   0.08985  -0.0480   0.8286   0.0119
  -9.500  -0.3171   0.08810   0.08587  -0.0500   0.8271   0.0119
  -9.250  -0.3303   0.08160   0.07940  -0.0529   0.8253   0.0123
  -9.000  -0.3293   0.07808   0.07588  -0.0547   0.8237   0.0124
  -8.750  -0.3254   0.07549   0.07329  -0.0560   0.8220   0.0126
  -8.500  -0.3273   0.07178   0.06960  -0.0580   0.8200   0.0127
  -8.250  -0.3291   0.06865   0.06647  -0.0597   0.8177   0.0129
  -8.000  -0.3446   0.06330   0.06117  -0.0639   0.8154   0.0128
  -7.750  -0.3464   0.05771   0.05555  -0.0689   0.8131   0.0129
  -7.500  -0.3436   0.05255   0.05031  -0.0724   0.8109   0.0131
  -7.250  -0.3385   0.04747   0.04509  -0.0748   0.8089   0.0134
  -7.000  -0.3310   0.04249   0.03993  -0.0763   0.8071   0.0138
  -6.750  -0.3209   0.03766   0.03488  -0.0770   0.8054   0.0143
  -6.000  -0.2893   0.01927   0.01465  -0.0737   0.8003   0.0122
  -5.750  -0.2682   0.01637   0.01147  -0.0729   0.7987   0.0111
  -5.500  -0.2439   0.01474   0.00959  -0.0724   0.7971   0.0110
  -5.250  -0.2183   0.01360   0.00828  -0.0720   0.7955   0.0111
  -5.000  -0.1918   0.01285   0.00740  -0.0717   0.7940   0.0115
  -4.750  -0.1647   0.01237   0.00683  -0.0716   0.7924   0.0118
  -4.500  -0.1382   0.01172   0.00608  -0.0713   0.7909   0.0121
  -4.250  -0.1131   0.01083   0.00508  -0.0709   0.7890   0.0124
  -4.000  -0.0863   0.01026   0.00446  -0.0707   0.7875   0.0129
  -3.750  -0.0589   0.00985   0.00403  -0.0707   0.7856   0.0134
  -3.500  -0.0312   0.00952   0.00367  -0.0707   0.7836   0.0139
  -3.250  -0.0034   0.00926   0.00338  -0.0706   0.7815   0.0148
  -3.000   0.0245   0.00901   0.00309  -0.0706   0.7795   0.0157
  -2.750   0.0523   0.00873   0.00274  -0.0705   0.7775   0.0171
  -2.500   0.0801   0.00850   0.00249  -0.0704   0.7754   0.0205
  -2.250   0.1077   0.00818   0.00229  -0.0704   0.7732   0.0458
  -2.000   0.1356   0.00792   0.00215  -0.0705   0.7706   0.0770
  -1.750   0.1633   0.00766   0.00201  -0.0706   0.7676   0.1148
  -1.500   0.1906   0.00732   0.00188  -0.0706   0.7647   0.1788
  -1.250   0.2172   0.00691   0.00176  -0.0705   0.7620   0.2807
  -1.000   0.2438   0.00656   0.00170  -0.0704   0.7593   0.3826
  -0.750   0.2703   0.00617   0.00166  -0.0704   0.7564   0.4922
  -0.500   0.2957   0.00575   0.00163  -0.0700   0.7532   0.6231
  -0.250   0.3210   0.00541   0.00159  -0.0694   0.7502   0.7239
   0.000   0.3444   0.00507   0.00157  -0.0683   0.7473   0.8355
   0.250   0.3758   0.00484   0.00160  -0.0687   0.7442   0.9392
   0.500   0.4259   0.00481   0.00159  -0.0735   0.7407   0.9744
   0.750   0.4675   0.00481   0.00155  -0.0765   0.7369   0.9885
   1.000   0.5123   0.00479   0.00149  -0.0802   0.7332   0.9967
   1.250   0.5513   0.00477   0.00145  -0.0827   0.7285   1.0000
   1.500   0.5778   0.00475   0.00142  -0.0824   0.7223   1.0000
   1.750   0.6041   0.00475   0.00138  -0.0821   0.7146   1.0000
   2.000   0.6305   0.00475   0.00134  -0.0818   0.7050   1.0000
   2.250   0.6571   0.00476   0.00134  -0.0816   0.6943   1.0000
   2.500   0.6835   0.00480   0.00135  -0.0814   0.6830   1.0000
   2.750   0.7098   0.00487   0.00137  -0.0811   0.6700   1.0000
   3.000   0.7360   0.00496   0.00141  -0.0808   0.6558   1.0000
   3.250   0.7619   0.00508   0.00147  -0.0805   0.6397   1.0000
   3.500   0.7877   0.00523   0.00155  -0.0802   0.6234   1.0000
   3.750   0.8131   0.00540   0.00166  -0.0798   0.6055   1.0000
   4.000   0.8386   0.00557   0.00177  -0.0794   0.5873   1.0000
   4.250   0.8635   0.00579   0.00191  -0.0790   0.5650   1.0000
   4.500   0.8872   0.00611   0.00210  -0.0784   0.5335   1.0000
   4.750   0.9100   0.00647   0.00232  -0.0776   0.4966   1.0000
   5.000   0.9326   0.00684   0.00254  -0.0769   0.4637   1.0000
   5.250   0.9543   0.00725   0.00280  -0.0760   0.4290   1.0000
   5.500   0.9764   0.00762   0.00304  -0.0751   0.4004   1.0000
   5.750   0.9976   0.00803   0.00333  -0.0742   0.3683   1.0000
   6.000   1.0185   0.00845   0.00361  -0.0731   0.3374   1.0000
   6.250   1.0384   0.00891   0.00392  -0.0720   0.3041   1.0000
   6.500   1.0566   0.00946   0.00429  -0.0706   0.2651   1.0000
   6.750   1.0742   0.01003   0.00469  -0.0691   0.2308   1.0000
   7.000   1.0919   0.01057   0.00508  -0.0676   0.2016   1.0000
   7.250   1.1092   0.01109   0.00547  -0.0660   0.1753   1.0000
   7.500   1.1269   0.01157   0.00586  -0.0645   0.1537   1.0000
   7.750   1.1428   0.01211   0.00628  -0.0628   0.1323   1.0000
   8.000   1.1568   0.01265   0.00673  -0.0607   0.1112   1.0000
   8.250   1.1659   0.01328   0.00725  -0.0577   0.0906   1.0000
   8.500   1.1765   0.01394   0.00781  -0.0552   0.0736   1.0000
   8.750   1.1889   0.01459   0.00840  -0.0531   0.0607   1.0000
   9.000   1.2032   0.01519   0.00896  -0.0514   0.0518   1.0000
   9.250   1.2178   0.01580   0.00955  -0.0497   0.0450   1.0000
   9.500   1.2329   0.01641   0.01016  -0.0482   0.0402   1.0000
   9.750   1.2476   0.01706   0.01081  -0.0466   0.0356   1.0000
  10.000   1.2637   0.01763   0.01141  -0.0453   0.0329   1.0000
  10.250   1.2771   0.01839   0.01215  -0.0437   0.0290   1.0000
  10.500   1.2923   0.01905   0.01285  -0.0424   0.0269   1.0000
  10.750   1.3080   0.01968   0.01351  -0.0412   0.0249   1.0000
  11.000   1.3211   0.02049   0.01433  -0.0397   0.0225   1.0000
  11.250   1.3328   0.02142   0.01530  -0.0381   0.0204   1.0000
  11.500   1.3483   0.02208   0.01601  -0.0369   0.0192   1.0000
  11.750   1.3615   0.02293   0.01687  -0.0356   0.0175   1.0000
  12.000   1.3686   0.02422   0.01820  -0.0337   0.0153   1.0000
  12.250   1.3833   0.02498   0.01901  -0.0326   0.0145   1.0000
  12.500   1.3953   0.02593   0.02001  -0.0313   0.0137   1.0000
  12.750   1.4068   0.02694   0.02104  -0.0301   0.0124   1.0000
  13.000   1.4107   0.02857   0.02274  -0.0282   0.0111   1.0000
  13.250   1.4218   0.02964   0.02387  -0.0270   0.0107   1.0000
  13.500   1.4317   0.03084   0.02513  -0.0258   0.0101   1.0000
  13.750   1.4411   0.03209   0.02644  -0.0246   0.0097   1.0000
  14.000   1.4477   0.03360   0.02803  -0.0233   0.0094   1.0000
  14.250   1.4548   0.03510   0.02958  -0.0222   0.0088   1.0000
  14.500   1.4588   0.03695   0.03150  -0.0210   0.0083   1.0000
  14.750   1.4523   0.03986   0.03453  -0.0194   0.0079   1.0000
  15.000   1.4571   0.04181   0.03657  -0.0185   0.0078   1.0000
  15.250   1.4638   0.04361   0.03848  -0.0179   0.0075   1.0000
  15.500   1.4667   0.04586   0.04082  -0.0172   0.0074   1.0000
  15.750   1.4717   0.04795   0.04299  -0.0168   0.0071   1.0000
  16.000   1.4731   0.05051   0.04565  -0.0164   0.0069   1.0000
  16.250   1.4765   0.05293   0.04815  -0.0162   0.0067   1.0000
  16.500   1.4720   0.05638   0.05172  -0.0161   0.0066   1.0000
  16.750   1.4737   0.05917   0.05459  -0.0162   0.0063   1.0000
  17.000   1.4721   0.06246   0.05797  -0.0166   0.0062   1.0000
  17.250   1.4672   0.06631   0.06192  -0.0171   0.0060   1.0000
  17.500   1.4575   0.07098   0.06670  -0.0181   0.0058   1.0000
  17.750   1.4474   0.07589   0.07174  -0.0193   0.0058   1.0000
  18.000   1.4338   0.08149   0.07748  -0.0210   0.0056   1.0000
  18.250   1.4126   0.08855   0.08470  -0.0234   0.0055   1.0000
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