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E195 (11.82%) (e195-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 200,000
Max Cl/Cd: 80.09 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e195-il-200000.txt
Download as CSV file: xf-e195-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E195  (11.82%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3714   0.09031   0.08693  -0.0442   1.0000   0.0608
  -9.000  -0.3987   0.08445   0.08122  -0.0524   1.0000   0.0621
  -8.750  -0.4178   0.07959   0.07645  -0.0565   1.0000   0.0622
  -8.500  -0.4429   0.07630   0.07316  -0.0569   1.0000   0.0623
  -8.250  -0.4673   0.07415   0.07102  -0.0546   1.0000   0.0624
  -8.000  -0.3231   0.06250   0.05976  -0.0486   0.9940   0.0725
  -7.750  -0.4405   0.06689   0.06401  -0.0529   0.9951   0.0652
  -7.500  -0.4139   0.06222   0.05926  -0.0593   0.9865   0.0677
  -7.250  -0.4047   0.05132   0.04759  -0.0753   0.9685   0.0763
  -7.000  -0.3725   0.04811   0.04455  -0.0773   0.9620   0.0787
  -6.750  -0.3639   0.03199   0.02642  -0.0808   0.9459   0.0399
  -6.500  -0.3379   0.02742   0.02153  -0.0820   0.9351   0.0379
  -6.250  -0.3089   0.02429   0.01793  -0.0828   0.9248   0.0369
  -6.000  -0.2790   0.02195   0.01519  -0.0832   0.9142   0.0367
  -5.750  -0.2517   0.02025   0.01319  -0.0830   0.9012   0.0371
  -5.500  -0.2248   0.01892   0.01163  -0.0825   0.8884   0.0378
  -5.250  -0.1982   0.01809   0.01058  -0.0819   0.8760   0.0393
  -5.000  -0.1745   0.01667   0.00910  -0.0812   0.8642   0.0422
  -4.750  -0.1498   0.01586   0.00822  -0.0804   0.8534   0.0447
  -4.500  -0.1258   0.01519   0.00745  -0.0795   0.8419   0.0483
  -4.250  -0.1027   0.01438   0.00659  -0.0785   0.8311   0.0553
  -4.000  -0.0797   0.01342   0.00576  -0.0775   0.8220   0.0931
  -3.750  -0.0567   0.01266   0.00534  -0.0769   0.8125   0.1784
  -3.500  -0.0327   0.01221   0.00511  -0.0764   0.8035   0.2500
  -3.250  -0.0090   0.01173   0.00494  -0.0758   0.7957   0.3447
  -3.000   0.0143   0.01142   0.00492  -0.0750   0.7870   0.4387
  -2.750   0.0389   0.01122   0.00485  -0.0742   0.7802   0.5082
  -2.500   0.0634   0.01108   0.00481  -0.0735   0.7720   0.5606
  -2.250   0.0885   0.01096   0.00474  -0.0727   0.7656   0.6114
  -2.000   0.1125   0.01083   0.00476  -0.0717   0.7581   0.6623
  -1.750   0.1370   0.01071   0.00472  -0.0706   0.7518   0.7129
  -1.500   0.1609   0.01061   0.00474  -0.0694   0.7451   0.7642
  -1.250   0.1854   0.01052   0.00476  -0.0681   0.7388   0.8203
  -1.000   0.2153   0.01051   0.00479  -0.0678   0.7334   0.8783
  -0.750   0.2560   0.01057   0.00482  -0.0699   0.7266   0.9270
  -0.500   0.3044   0.01065   0.00476  -0.0738   0.7213   0.9599
  -0.250   0.3569   0.01072   0.00474  -0.0790   0.7149   0.9828
   0.000   0.4142   0.01071   0.00459  -0.0853   0.7089   0.9994
   0.250   0.4368   0.01080   0.00457  -0.0846   0.7035   1.0000
   0.500   0.4581   0.01090   0.00463  -0.0837   0.6969   1.0000
   0.750   0.4815   0.01101   0.00464  -0.0829   0.6918   1.0000
   1.000   0.5042   0.01117   0.00476  -0.0821   0.6857   1.0000
   1.250   0.5278   0.01130   0.00485  -0.0814   0.6799   1.0000
   1.500   0.5529   0.01146   0.00491  -0.0809   0.6753   1.0000
   1.750   0.5758   0.01163   0.00510  -0.0801   0.6686   1.0000
   2.000   0.6007   0.01177   0.00519  -0.0796   0.6634   1.0000
   2.250   0.6253   0.01196   0.00537  -0.0790   0.6581   1.0000
   2.500   0.6493   0.01214   0.00555  -0.0783   0.6518   1.0000
   2.750   0.6752   0.01229   0.00564  -0.0779   0.6470   1.0000
   3.000   0.6989   0.01249   0.00590  -0.0772   0.6405   1.0000
   3.250   0.7242   0.01264   0.00604  -0.0767   0.6345   1.0000
   3.500   0.7496   0.01281   0.00620  -0.0762   0.6286   1.0000
   3.750   0.7740   0.01296   0.00639  -0.0756   0.6214   1.0000
   4.000   0.8006   0.01308   0.00649  -0.0752   0.6155   1.0000
   4.250   0.8243   0.01321   0.00670  -0.0744   0.6071   1.0000
   4.500   0.8509   0.01331   0.00676  -0.0740   0.6005   1.0000
   4.750   0.8747   0.01342   0.00696  -0.0733   0.5916   1.0000
   5.000   0.9004   0.01351   0.00707  -0.0727   0.5838   1.0000
   5.250   0.9254   0.01356   0.00716  -0.0721   0.5747   1.0000
   5.500   0.9496   0.01364   0.00732  -0.0713   0.5651   1.0000
   5.750   0.9753   0.01367   0.00736  -0.0707   0.5559   1.0000
   6.000   0.9993   0.01370   0.00747  -0.0699   0.5450   1.0000
   6.250   1.0228   0.01375   0.00761  -0.0690   0.5331   1.0000
   6.500   1.0463   0.01379   0.00772  -0.0681   0.5203   1.0000
   6.750   1.0691   0.01382   0.00783  -0.0670   0.5054   1.0000
   7.000   1.0914   0.01387   0.00793  -0.0658   0.4885   1.0000
   7.250   1.1128   0.01397   0.00807  -0.0645   0.4684   1.0000
   7.500   1.1317   0.01413   0.00823  -0.0628   0.4396   1.0000
   7.750   1.1476   0.01447   0.00848  -0.0607   0.3991   1.0000
   8.000   1.1598   0.01511   0.00891  -0.0581   0.3457   1.0000
   8.250   1.1654   0.01616   0.00961  -0.0547   0.2840   1.0000
   8.500   1.1689   0.01741   0.01053  -0.0513   0.2292   1.0000
   8.750   1.1711   0.01871   0.01155  -0.0477   0.1831   1.0000
   9.000   1.1723   0.01989   0.01255  -0.0440   0.1475   1.0000
   9.250   1.1716   0.02122   0.01368  -0.0402   0.1167   1.0000
   9.500   1.1707   0.02270   0.01499  -0.0367   0.0865   1.0000
   9.750   1.1646   0.02465   0.01675  -0.0331   0.0581   1.0000
  10.000   1.1547   0.02711   0.01909  -0.0296   0.0401   1.0000
  10.250   1.1483   0.02952   0.02148  -0.0269   0.0346   1.0000
  10.500   1.1518   0.03133   0.02342  -0.0252   0.0316   1.0000
  10.750   1.1536   0.03337   0.02553  -0.0237   0.0292   1.0000
  11.000   1.1511   0.03586   0.02804  -0.0221   0.0273   1.0000
  11.250   1.1520   0.03817   0.03042  -0.0207   0.0262   1.0000
  11.500   1.1586   0.04002   0.03239  -0.0197   0.0247   1.0000
  11.750   1.1651   0.04192   0.03437  -0.0188   0.0234   1.0000
  12.000   1.1713   0.04393   0.03644  -0.0177   0.0226   1.0000
  12.250   1.1786   0.04588   0.03848  -0.0167   0.0220   1.0000
  12.500   1.1867   0.04790   0.04052  -0.0156   0.0211   1.0000
  12.750   1.2014   0.04978   0.04244  -0.0142   0.0206   1.0000
  13.000   1.2203   0.05197   0.04475  -0.0128   0.0202   1.0000
  13.250   1.2305   0.05432   0.04731  -0.0119   0.0200   1.0000
  13.500   1.2385   0.05705   0.05026  -0.0111   0.0199   1.0000
  13.750   1.2407   0.06018   0.05363  -0.0105   0.0198   1.0000
  14.000   1.2422   0.06366   0.05735  -0.0101   0.0199   1.0000
  14.250   1.2385   0.06761   0.06155  -0.0098   0.0199   1.0000
  14.500   1.2320   0.07189   0.06606  -0.0099   0.0200   1.0000
  14.750   1.2222   0.07667   0.07108  -0.0103   0.0201   1.0000
  15.000   1.2103   0.08186   0.07650  -0.0111   0.0202   1.0000
  15.250   1.2004   0.08648   0.08136  -0.0122   0.0203   1.0000
  15.500   1.1858   0.09163   0.08671  -0.0140   0.0204   1.0000
  15.750   1.1707   0.09706   0.09234  -0.0163   0.0204   1.0000
  16.000   1.1561   0.10262   0.09811  -0.0191   0.0206   1.0000
  16.250   1.1368   0.10960   0.10529  -0.0228   0.0206   1.0000
  16.500   1.1047   0.11978   0.11581  -0.0293   0.0214   1.0000
  16.750   1.0345   0.14111   0.13760  -0.0438   0.0228   1.0000
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