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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 100,000
Max Cl/Cd: 61.41 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e174-il-100000-n5.txt
Download as CSV file: xf-e174-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E174  (Dicke 8.92%)                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3506   0.10247   0.09767  -0.0309   1.0000   0.0498
  -8.500  -0.3524   0.09992   0.09521  -0.0341   1.0000   0.0502
  -8.250  -0.3535   0.09712   0.09250  -0.0365   1.0000   0.0504
  -8.000  -0.3551   0.09423   0.08970  -0.0384   1.0000   0.0505
  -7.750  -0.3541   0.09085   0.08640  -0.0415   1.0000   0.0506
  -7.500  -0.3507   0.08638   0.08203  -0.0409   1.0000   0.0510
  -7.250  -0.3466   0.08290   0.07861  -0.0396   1.0000   0.0515
  -7.000  -0.3452   0.07993   0.07572  -0.0393   1.0000   0.0519
  -6.750  -0.2530   0.05354   0.04950  -0.0553   0.9584   0.0287
  -6.500  -0.3102   0.06457   0.06023  -0.0569   0.9777   0.0291
  -6.250  -0.2882   0.06135   0.05698  -0.0590   0.9653   0.0276
  -6.000  -0.2607   0.05566   0.05117  -0.0662   0.9499   0.0262
  -5.750  -0.2313   0.04886   0.04411  -0.0740   0.9346   0.0246
  -5.500  -0.1998   0.03905   0.03345  -0.0819   0.9194   0.0221
  -5.250  -0.1725   0.03493   0.02890  -0.0846   0.9060   0.0218
  -5.000  -0.1449   0.03117   0.02458  -0.0864   0.8932   0.0217
  -4.750  -0.1169   0.02799   0.02081  -0.0874   0.8810   0.0218
  -4.500  -0.0892   0.02549   0.01779  -0.0880   0.8696   0.0226
  -4.250  -0.0627   0.02416   0.01625  -0.0882   0.8576   0.0246
  -4.000  -0.0355   0.02250   0.01419  -0.0880   0.8460   0.0259
  -3.750  -0.0080   0.02088   0.01219  -0.0877   0.8354   0.0268
  -3.500   0.0194   0.01956   0.01054  -0.0872   0.8260   0.0279
  -3.250   0.0459   0.01844   0.00924  -0.0867   0.8154   0.0294
  -3.000   0.0724   0.01759   0.00831  -0.0864   0.8057   0.0326
  -2.750   0.0995   0.01691   0.00747  -0.0860   0.7973   0.0398
  -2.500   0.1262   0.01619   0.00666  -0.0857   0.7876   0.0521
  -2.250   0.1527   0.01539   0.00607  -0.0855   0.7793   0.1064
  -2.000   0.1784   0.01463   0.00580  -0.0854   0.7709   0.2265
  -1.750   0.2040   0.01406   0.00559  -0.0851   0.7628   0.3568
  -1.500   0.2279   0.01340   0.00546  -0.0842   0.7552   0.5399
  -1.250   0.2466   0.01273   0.00543  -0.0814   0.7476   0.7597
  -1.000   0.2911   0.01235   0.00506  -0.0838   0.7407   1.0000
  -0.750   0.3180   0.01247   0.00493  -0.0836   0.7330   1.0000
  -0.500   0.3450   0.01259   0.00481  -0.0834   0.7261   1.0000
  -0.250   0.3719   0.01273   0.00477  -0.0832   0.7188   1.0000
   0.000   0.3989   0.01286   0.00472  -0.0830   0.7120   1.0000
   0.250   0.4258   0.01302   0.00472  -0.0829   0.7052   1.0000
   0.500   0.4527   0.01317   0.00474  -0.0827   0.6984   1.0000
   0.750   0.4798   0.01333   0.00478  -0.0825   0.6921   1.0000
   1.000   0.5066   0.01350   0.00487  -0.0823   0.6852   1.0000
   1.250   0.5338   0.01367   0.00491  -0.0821   0.6796   1.0000
   1.500   0.5604   0.01387   0.00508  -0.0820   0.6723   1.0000
   1.750   0.5875   0.01404   0.00517  -0.0818   0.6667   1.0000
   2.000   0.6140   0.01426   0.00539  -0.0816   0.6596   1.0000
   2.250   0.6410   0.01444   0.00553  -0.0814   0.6536   1.0000
   2.500   0.6676   0.01466   0.00575  -0.0813   0.6470   1.0000
   2.750   0.6943   0.01487   0.00598  -0.0811   0.6404   1.0000
   3.000   0.7210   0.01508   0.00619  -0.0808   0.6342   1.0000
   3.250   0.7473   0.01531   0.00646  -0.0806   0.6270   1.0000
   3.500   0.7741   0.01551   0.00666  -0.0804   0.6207   1.0000
   3.750   0.8001   0.01575   0.00700  -0.0801   0.6124   1.0000
   4.000   0.8265   0.01594   0.00723  -0.0797   0.6049   1.0000
   4.250   0.8524   0.01613   0.00749  -0.0793   0.5959   1.0000
   4.500   0.8780   0.01633   0.00777  -0.0789   0.5861   1.0000
   4.750   0.9040   0.01648   0.00801  -0.0784   0.5765   1.0000
   5.000   0.9296   0.01663   0.00824  -0.0779   0.5656   1.0000
   5.250   0.9546   0.01680   0.00854  -0.0773   0.5534   1.0000
   5.500   0.9795   0.01696   0.00885  -0.0767   0.5404   1.0000
   5.750   1.0042   0.01711   0.00911  -0.0760   0.5259   1.0000
   6.000   1.0287   0.01726   0.00937  -0.0752   0.5099   1.0000
   6.250   1.0526   0.01742   0.00965  -0.0744   0.4917   1.0000
   6.500   1.0758   0.01764   0.01003  -0.0735   0.4696   1.0000
   6.750   1.0980   0.01788   0.01036  -0.0724   0.4419   1.0000
   7.000   1.1173   0.01826   0.01065  -0.0709   0.3946   1.0000
   7.250   1.1315   0.01909   0.01112  -0.0689   0.3198   1.0000
   7.500   1.1396   0.02064   0.01209  -0.0665   0.2354   1.0000
   7.750   1.1471   0.02238   0.01336  -0.0643   0.1659   1.0000
   8.000   1.1550   0.02408   0.01471  -0.0623   0.1106   1.0000
   8.250   1.1645   0.02560   0.01604  -0.0603   0.0749   1.0000
   8.500   1.1718   0.02727   0.01755  -0.0580   0.0485   1.0000
   8.750   1.1780   0.02895   0.01919  -0.0556   0.0371   1.0000
   9.000   1.1827   0.03051   0.02084  -0.0529   0.0324   1.0000
   9.250   1.1876   0.03209   0.02255  -0.0505   0.0293   1.0000
   9.500   1.1903   0.03391   0.02445  -0.0483   0.0272   1.0000
   9.750   1.1938   0.03578   0.02645  -0.0464   0.0254   1.0000
  10.000   1.1989   0.03761   0.02845  -0.0449   0.0239   1.0000
  10.250   1.2034   0.03959   0.03059  -0.0435   0.0224   1.0000
  10.500   1.2071   0.04176   0.03289  -0.0422   0.0216   1.0000
  10.750   1.2113   0.04397   0.03522  -0.0411   0.0210   1.0000
  11.000   1.2150   0.04637   0.03772  -0.0400   0.0204   1.0000
  11.250   1.2199   0.04889   0.04030  -0.0389   0.0199   1.0000
  11.500   1.2290   0.05117   0.04277  -0.0378   0.0195   1.0000
  11.750   1.2384   0.05355   0.04536  -0.0368   0.0192   1.0000
  12.000   1.2470   0.05618   0.04822  -0.0359   0.0188   1.0000
  12.250   1.2535   0.05909   0.05141  -0.0351   0.0186   1.0000
  12.500   1.2568   0.06234   0.05494  -0.0345   0.0183   1.0000
  12.750   1.2562   0.06591   0.05879  -0.0343   0.0180   1.0000
  13.000   1.2521   0.06983   0.06299  -0.0344   0.0177   1.0000
  13.250   1.2457   0.07400   0.06741  -0.0349   0.0173   1.0000
  13.500   1.2372   0.07860   0.07227  -0.0359   0.0171   1.0000
  13.750   1.2265   0.08361   0.07753  -0.0373   0.0169   1.0000
  14.000   1.2138   0.08907   0.08323  -0.0392   0.0167   1.0000
  14.250   1.1985   0.09526   0.08967  -0.0419   0.0167   1.0000
  14.500   1.1821   0.10197   0.09662  -0.0452   0.0167   1.0000
  14.750   1.1623   0.10993   0.10482  -0.0496   0.0169   1.0000
  15.000   1.1409   0.11893   0.11405  -0.0550   0.0171   1.0000
  15.250   1.1168   0.12955   0.12487  -0.0619   0.0175   1.0000
  15.500   1.0921   0.14158   0.13706  -0.0698   0.0181   1.0000
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