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E195 (11.82%) (e195-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 100,000
Max Cl/Cd: 55.88 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e195-il-100000.txt
Download as CSV file: xf-e195-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3548   0.10567   0.10076  -0.0354   1.0000   0.1109
  -9.500  -0.3714   0.10322   0.09843  -0.0395   1.0000   0.1158
  -9.250  -0.4068   0.10112   0.09653  -0.0459   1.0000   0.1168
  -9.000  -0.3581   0.09573   0.09102  -0.0388   1.0000   0.1206
  -8.750  -0.3530   0.09294   0.08828  -0.0386   1.0000   0.1245
  -8.500  -0.2854   0.08075   0.07662  -0.0403   1.0000   0.1345
  -8.250  -0.2841   0.07813   0.07408  -0.0389   1.0000   0.1381
  -8.000  -0.3000   0.07624   0.07233  -0.0373   1.0000   0.1416
  -7.750  -0.3324   0.07692   0.07321  -0.0318   1.0000   0.1422
  -7.500  -0.3810   0.07562   0.07207  -0.0350   0.9942   0.1449
  -7.250  -0.3519   0.06998   0.06641  -0.0358   0.9895   0.1487
  -7.000  -0.4820   0.07849   0.07471  -0.0343   0.9977   0.1447
  -6.750  -0.4545   0.07355   0.06978  -0.0365   0.9915   0.1491
  -6.500  -0.4326   0.06711   0.06318  -0.0478   0.9794   0.1621
  -6.250  -0.4224   0.04614   0.04090  -0.0636   0.9654   0.0793
  -6.000  -0.3933   0.03762   0.03081  -0.0672   0.9574   0.0629
  -5.750  -0.3652   0.03444   0.02713  -0.0684   0.9474   0.0629
  -5.500  -0.3296   0.03106   0.02342  -0.0711   0.9414   0.0648
  -5.250  -0.2968   0.02867   0.02062  -0.0723   0.9327   0.0653
  -5.000  -0.2524   0.02631   0.01792  -0.0753   0.9286   0.0672
  -4.750  -0.2217   0.02479   0.01619  -0.0757   0.9191   0.0704
  -4.500  -0.1784   0.02301   0.01425  -0.0784   0.9147   0.0777
  -4.250  -0.1496   0.02191   0.01316  -0.0785   0.9054   0.0903
  -4.000  -0.1135   0.02016   0.01163  -0.0799   0.9001   0.1311
  -3.750  -0.0917   0.01892   0.01097  -0.0793   0.8903   0.2228
  -3.500  -0.0601   0.01785   0.01059  -0.0804   0.8847   0.3647
  -3.250  -0.0403   0.01752   0.01061  -0.0788   0.8747   0.4676
  -3.000  -0.0088   0.01711   0.01040  -0.0787   0.8694   0.5612
  -2.750   0.0101   0.01706   0.01050  -0.0766   0.8595   0.6268
  -2.500   0.0400   0.01678   0.01035  -0.0758   0.8544   0.6958
  -2.250   0.0585   0.01683   0.01049  -0.0733   0.8449   0.7528
  -2.000   0.0893   0.01664   0.01035  -0.0723   0.8400   0.8165
  -1.750   0.1196   0.01678   0.01051  -0.0718   0.8318   0.8774
  -1.500   0.1817   0.01674   0.01028  -0.0772   0.8276   0.9316
  -1.250   0.2605   0.01654   0.00981  -0.0863   0.8245   0.9686
  -1.000   0.3417   0.01632   0.00936  -0.0976   0.8179   0.9998
  -0.750   0.3557   0.01634   0.00923  -0.0960   0.8104   1.0000
  -0.500   0.3658   0.01669   0.00948  -0.0939   0.8008   1.0000
  -0.250   0.3873   0.01678   0.00941  -0.0929   0.7949   1.0000
   0.000   0.4011   0.01726   0.00981  -0.0911   0.7856   1.0000
   0.250   0.4256   0.01738   0.00980  -0.0904   0.7801   1.0000
   0.500   0.4409   0.01792   0.01028  -0.0887   0.7712   1.0000
   0.750   0.4661   0.01808   0.01033  -0.0881   0.7658   1.0000
   1.000   0.4823   0.01866   0.01088  -0.0866   0.7573   1.0000
   1.250   0.5077   0.01886   0.01100  -0.0860   0.7517   1.0000
   1.500   0.5254   0.01946   0.01157  -0.0847   0.7439   1.0000
   1.750   0.5502   0.01971   0.01178  -0.0841   0.7379   1.0000
   2.000   0.5704   0.02025   0.01229  -0.0830   0.7309   1.0000
   2.250   0.5931   0.02064   0.01267  -0.0822   0.7241   1.0000
   2.500   0.6188   0.02093   0.01295  -0.0817   0.7186   1.0000
   2.750   0.6367   0.02160   0.01365  -0.0805   0.7102   1.0000
   3.000   0.6669   0.02166   0.01367  -0.0804   0.7057   1.0000
   3.250   0.6812   0.02256   0.01464  -0.0789   0.6962   1.0000
   3.500   0.7119   0.02257   0.01465  -0.0788   0.6914   1.0000
   3.750   0.7267   0.02345   0.01561  -0.0773   0.6817   1.0000
   4.000   0.7583   0.02337   0.01553  -0.0772   0.6767   1.0000
   4.250   0.7734   0.02424   0.01651  -0.0757   0.6667   1.0000
   4.500   0.8068   0.02400   0.01628  -0.0757   0.6615   1.0000
   4.750   0.8224   0.02477   0.01716  -0.0742   0.6508   1.0000
   5.000   0.8522   0.02468   0.01710  -0.0738   0.6439   1.0000
   5.250   0.8753   0.02492   0.01745  -0.0727   0.6342   1.0000
   5.500   0.8967   0.02524   0.01788  -0.0715   0.6241   1.0000
   5.750   0.9328   0.02458   0.01723  -0.0715   0.6169   1.0000
   6.000   0.9533   0.02480   0.01761  -0.0701   0.6049   1.0000
   6.250   0.9775   0.02475   0.01766  -0.0689   0.5934   1.0000
   6.500   1.0059   0.02435   0.01735  -0.0680   0.5820   1.0000
   6.750   1.0367   0.02371   0.01678  -0.0673   0.5702   1.0000
   7.000   1.0651   0.02316   0.01633  -0.0664   0.5566   1.0000
   7.250   1.0888   0.02281   0.01609  -0.0649   0.5408   1.0000
   7.500   1.1110   0.02244   0.01587  -0.0631   0.5229   1.0000
   7.750   1.1348   0.02188   0.01540  -0.0615   0.5029   1.0000
   8.000   1.1547   0.02150   0.01515  -0.0594   0.4794   1.0000
   8.250   1.1720   0.02125   0.01499  -0.0569   0.4507   1.0000
   8.500   1.1853   0.02121   0.01495  -0.0539   0.4134   1.0000
   8.750   1.1906   0.02165   0.01526  -0.0500   0.3613   1.0000
   9.000   1.1870   0.02276   0.01594  -0.0453   0.2990   1.0000
   9.250   1.1773   0.02433   0.01710  -0.0402   0.2461   1.0000
   9.500   1.1661   0.02615   0.01859  -0.0354   0.2045   1.0000
   9.750   1.1565   0.02820   0.02037  -0.0315   0.1716   1.0000
  10.000   1.1474   0.03052   0.02248  -0.0283   0.1416   1.0000
  10.250   1.1378   0.03315   0.02487  -0.0255   0.1164   1.0000
  10.500   1.1294   0.03599   0.02756  -0.0232   0.0927   1.0000
  10.750   1.1221   0.03900   0.03039  -0.0208   0.0752   1.0000
  11.000   1.1219   0.04161   0.03291  -0.0189   0.0633   1.0000
  11.250   1.1275   0.04375   0.03500  -0.0175   0.0561   1.0000
  11.500   1.1407   0.04572   0.03703  -0.0159   0.0501   1.0000
  11.750   1.1587   0.04747   0.03878  -0.0147   0.0466   1.0000
  12.000   1.1968   0.04984   0.04112  -0.0138   0.0433   1.0000
  12.250   1.2165   0.05246   0.04409  -0.0128   0.0421   1.0000
  12.500   1.2268   0.05545   0.04740  -0.0117   0.0409   1.0000
  12.750   1.2307   0.05853   0.05078  -0.0106   0.0401   1.0000
  13.000   1.2298   0.06183   0.05437  -0.0095   0.0393   1.0000
  13.250   1.2256   0.06528   0.05809  -0.0088   0.0387   1.0000
  13.500   1.2173   0.06920   0.06228  -0.0082   0.0384   1.0000
  13.750   1.2092   0.07298   0.06628  -0.0081   0.0377   1.0000
  14.000   1.1901   0.07812   0.07176  -0.0085   0.0382   1.0000
  14.250   1.1700   0.08356   0.07749  -0.0095   0.0385   1.0000
  14.500   1.1473   0.08958   0.08378  -0.0114   0.0388   1.0000
  14.750   1.1227   0.09623   0.09069  -0.0140   0.0392   1.0000
  15.000   1.0950   0.10395   0.09864  -0.0177   0.0399   1.0000
  15.250   1.0678   0.11243   0.10733  -0.0223   0.0410   1.0000
  15.500   1.0402   0.12179   0.11685  -0.0280   0.0417   1.0000
  15.750   1.0180   0.13110   0.12625  -0.0334   0.0427   1.0000
  16.000   1.0009   0.14007   0.13527  -0.0385   0.0435   1.0000
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