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E374 (e374-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E374 (e374-il)
Reynolds number: 200,000
Max Cl/Cd: 75 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e374-il-200000.txt
Download as CSV file: xf-e374-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E374                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3419   0.10119   0.09789  -0.0319   1.0000   0.0455
 -10.250  -0.3395   0.09763   0.09435  -0.0325   1.0000   0.0470
 -10.000  -0.4466   0.09883   0.09536  -0.0352   1.0000   0.0435
  -9.750  -0.4394   0.09600   0.09253  -0.0345   1.0000   0.0445
  -9.500  -0.4345   0.09310   0.08966  -0.0345   1.0000   0.0459
  -9.250  -0.4342   0.08952   0.08611  -0.0358   1.0000   0.0467
  -9.000  -0.4356   0.08576   0.08240  -0.0374   1.0000   0.0481
  -8.750  -0.4400   0.08164   0.07833  -0.0396   1.0000   0.0491
  -8.500  -0.4500   0.07687   0.07363  -0.0430   1.0000   0.0505
  -8.250  -0.4677   0.07215   0.06897  -0.0462   1.0000   0.0510
  -8.000  -0.4843   0.06834   0.06515  -0.0461   1.0000   0.0514
  -7.750  -0.5072   0.06433   0.06098  -0.0462   1.0000   0.0534
  -7.500  -0.5272   0.06277   0.05916  -0.0427   1.0000   0.0542
  -7.250  -0.5433   0.06137   0.05764  -0.0380   1.0000   0.0543
  -6.250  -0.4760   0.03347   0.02789  -0.0433   0.9729   0.0318
  -6.000  -0.4482   0.02947   0.02340  -0.0445   0.9646   0.0319
  -5.750  -0.4136   0.02602   0.01955  -0.0461   0.9589   0.0308
  -5.500  -0.3805   0.02290   0.01595  -0.0472   0.9519   0.0306
  -5.250  -0.3435   0.02081   0.01349  -0.0488   0.9457   0.0312
  -5.000  -0.3097   0.01807   0.01058  -0.0499   0.9389   0.0334
  -4.750  -0.2746   0.01710   0.00957  -0.0514   0.9310   0.0400
  -4.500  -0.2450   0.01560   0.00802  -0.0516   0.9212   0.0462
  -4.250  -0.2146   0.01461   0.00701  -0.0521   0.9122   0.0604
  -4.000  -0.1886   0.01367   0.00614  -0.0517   0.9013   0.0879
  -3.750  -0.1669   0.01270   0.00548  -0.0506   0.8895   0.1547
  -3.500  -0.1465   0.01185   0.00510  -0.0494   0.8783   0.2676
  -3.250  -0.1286   0.01102   0.00484  -0.0477   0.8681   0.4133
  -3.000  -0.1143   0.01018   0.00470  -0.0448   0.8581   0.5911
  -2.750  -0.0955   0.00978   0.00485  -0.0420   0.8482   0.7505
  -2.500  -0.0677   0.00980   0.00493  -0.0409   0.8404   0.8280
  -2.250  -0.0359   0.00996   0.00502  -0.0408   0.8320   0.8723
  -2.000   0.0024   0.01021   0.00513  -0.0420   0.8249   0.9028
  -1.750   0.0458   0.01052   0.00528  -0.0443   0.8175   0.9238
  -1.500   0.0972   0.01080   0.00538  -0.0485   0.8110   0.9377
  -1.250   0.1486   0.01101   0.00544  -0.0530   0.8037   0.9496
  -1.000   0.1964   0.01115   0.00544  -0.0569   0.7969   0.9609
  -0.750   0.2425   0.01124   0.00540  -0.0607   0.7892   0.9722
  -0.500   0.2896   0.01125   0.00531  -0.0648   0.7824   0.9822
  -0.250   0.3388   0.01112   0.00508  -0.0695   0.7748   0.9909
   0.000   0.3856   0.01096   0.00484  -0.0739   0.7679   0.9990
   0.250   0.4101   0.01094   0.00477  -0.0736   0.7600   1.0000
   0.500   0.4315   0.01097   0.00476  -0.0727   0.7527   1.0000
   0.750   0.4530   0.01099   0.00474  -0.0718   0.7452   1.0000
   1.000   0.4746   0.01104   0.00477  -0.0709   0.7380   1.0000
   1.250   0.4964   0.01109   0.00478  -0.0700   0.7308   1.0000
   1.500   0.5182   0.01115   0.00485  -0.0690   0.7237   1.0000
   1.750   0.5402   0.01120   0.00489  -0.0681   0.7165   1.0000
   2.000   0.5621   0.01128   0.00496  -0.0671   0.7091   1.0000
   2.250   0.5843   0.01133   0.00500  -0.0661   0.7016   1.0000
   2.500   0.6058   0.01141   0.00512  -0.0651   0.6933   1.0000
   2.750   0.6285   0.01146   0.00513  -0.0640   0.6857   1.0000
   3.000   0.6495   0.01153   0.00525  -0.0628   0.6761   1.0000
   3.250   0.6718   0.01160   0.00532  -0.0617   0.6678   1.0000
   3.500   0.6938   0.01166   0.00541  -0.0606   0.6586   1.0000
   3.750   0.7151   0.01173   0.00554  -0.0593   0.6487   1.0000
   4.000   0.7375   0.01179   0.00560  -0.0581   0.6392   1.0000
   4.250   0.7597   0.01183   0.00565  -0.0569   0.6288   1.0000
   4.500   0.7808   0.01188   0.00579  -0.0556   0.6171   1.0000
   4.750   0.8022   0.01192   0.00590  -0.0542   0.6051   1.0000
   5.000   0.8236   0.01196   0.00599  -0.0528   0.5921   1.0000
   5.250   0.8446   0.01198   0.00606  -0.0513   0.5773   1.0000
   5.500   0.8653   0.01200   0.00613  -0.0497   0.5604   1.0000
   5.750   0.8857   0.01206   0.00623  -0.0481   0.5421   1.0000
   6.000   0.9041   0.01212   0.00630  -0.0461   0.5147   1.0000
   6.250   0.9202   0.01227   0.00639  -0.0437   0.4742   1.0000
   6.500   0.9344   0.01262   0.00659  -0.0410   0.4208   1.0000
   6.750   0.9453   0.01324   0.00694  -0.0379   0.3573   1.0000
   7.000   0.9514   0.01422   0.00756  -0.0342   0.2836   1.0000
   7.250   0.9559   0.01537   0.00832  -0.0305   0.2143   1.0000
   7.500   0.9594   0.01666   0.00920  -0.0268   0.1479   1.0000
   7.750   0.9589   0.01824   0.01033  -0.0225   0.0862   1.0000
   8.000   0.9581   0.01984   0.01171  -0.0180   0.0580   1.0000
   8.250   0.9602   0.02115   0.01299  -0.0140   0.0487   1.0000
   8.500   0.9672   0.02207   0.01399  -0.0107   0.0432   1.0000
   8.750   0.9712   0.02320   0.01514  -0.0072   0.0395   1.0000
   9.000   0.9718   0.02495   0.01689  -0.0035   0.0369   1.0000
   9.250   0.9836   0.02602   0.01809  -0.0014   0.0346   1.0000
   9.500   0.9949   0.02717   0.01934   0.0006   0.0316   1.0000
   9.750   1.0063   0.02859   0.02078   0.0024   0.0295   1.0000
  10.000   1.0334   0.03176   0.02399   0.0024   0.0274   1.0000
  10.250   1.0481   0.03308   0.02552   0.0041   0.0262   1.0000
  10.500   1.0625   0.03470   0.02736   0.0056   0.0246   1.0000
  10.750   1.0757   0.03650   0.02933   0.0071   0.0233   1.0000
  11.000   1.0884   0.03881   0.03186   0.0086   0.0224   1.0000
  11.250   1.0972   0.04142   0.03472   0.0103   0.0220   1.0000
  11.500   1.1015   0.04437   0.03797   0.0123   0.0219   1.0000
  11.750   1.1000   0.04750   0.04142   0.0145   0.0218   1.0000
  12.000   1.0870   0.05143   0.04576   0.0172   0.0223   1.0000
  12.250   1.0690   0.05574   0.05045   0.0193   0.0230   1.0000
  12.500   1.0502   0.06022   0.05523   0.0206   0.0235   1.0000
  12.750   1.0304   0.06486   0.06013   0.0210   0.0239   1.0000
  13.000   1.0096   0.06988   0.06537   0.0205   0.0244   1.0000
  13.250   0.9883   0.07520   0.07086   0.0192   0.0248   1.0000
  13.500   0.9672   0.08091   0.07675   0.0172   0.0252   1.0000
  13.750   0.9444   0.08734   0.08333   0.0142   0.0255   1.0000
  14.000   0.9203   0.09462   0.09076   0.0102   0.0256   1.0000
  14.250   0.8986   0.10226   0.09852   0.0057   0.0259   1.0000
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