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E374 (e374-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E374 (e374-il)
Reynolds number: 200,000
Max Cl/Cd: 71.85 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e374-il-200000-n5.txt
Download as CSV file: xf-e374-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4570   0.08716   0.08368  -0.0357   1.0000   0.0113
  -9.500  -0.4658   0.08130   0.07788  -0.0386   1.0000   0.0110
  -9.250  -0.4768   0.07510   0.07175  -0.0422   1.0000   0.0107
  -9.000  -0.4962   0.06680   0.06352  -0.0490   1.0000   0.0104
  -8.750  -0.5388   0.05678   0.05341  -0.0517   1.0000   0.0099
  -8.500  -0.5739   0.04884   0.04520  -0.0492   1.0000   0.0095
  -8.250  -0.5907   0.04442   0.04051  -0.0459   1.0000   0.0093
  -8.000  -0.6003   0.04109   0.03691  -0.0423   1.0000   0.0092
  -7.750  -0.5878   0.03554   0.03077  -0.0438   0.9884   0.0093
  -7.500  -0.5702   0.03131   0.02598  -0.0446   0.9766   0.0094
  -7.250  -0.5486   0.02813   0.02236  -0.0451   0.9647   0.0097
  -7.000  -0.5226   0.02587   0.01975  -0.0459   0.9536   0.0102
  -6.750  -0.4945   0.02363   0.01712  -0.0466   0.9430   0.0105
  -6.500  -0.4648   0.02217   0.01537  -0.0475   0.9314   0.0116
  -6.250  -0.4339   0.02084   0.01372  -0.0483   0.9197   0.0132
  -6.000  -0.4034   0.01937   0.01196  -0.0489   0.9077   0.0140
  -5.750  -0.3754   0.01787   0.01027  -0.0492   0.8947   0.0147
  -5.500  -0.3485   0.01682   0.00911  -0.0492   0.8811   0.0160
  -5.250  -0.3223   0.01602   0.00818  -0.0489   0.8677   0.0180
  -5.000  -0.2973   0.01530   0.00731  -0.0484   0.8546   0.0214
  -4.750  -0.2725   0.01475   0.00664  -0.0478   0.8423   0.0265
  -4.500  -0.2487   0.01412   0.00592  -0.0470   0.8305   0.0337
  -4.250  -0.2245   0.01367   0.00543  -0.0463   0.8190   0.0465
  -4.000  -0.2004   0.01323   0.00498  -0.0457   0.8085   0.0658
  -3.750  -0.1761   0.01283   0.00459  -0.0450   0.7989   0.0911
  -3.500  -0.1524   0.01241   0.00427  -0.0443   0.7894   0.1306
  -3.250  -0.1292   0.01197   0.00398  -0.0436   0.7804   0.1860
  -3.000  -0.1067   0.01148   0.00373  -0.0428   0.7723   0.2638
  -2.750  -0.0852   0.01098   0.00353  -0.0418   0.7638   0.3552
  -2.500  -0.0644   0.01049   0.00335  -0.0405   0.7562   0.4536
  -2.250  -0.0447   0.01000   0.00322  -0.0389   0.7486   0.5619
  -2.000  -0.0247   0.00958   0.00322  -0.0369   0.7417   0.6857
  -1.750   0.0004   0.00943   0.00328  -0.0358   0.7346   0.7734
  -1.500   0.0291   0.00942   0.00330  -0.0355   0.7284   0.8230
  -1.250   0.0597   0.00947   0.00330  -0.0356   0.7216   0.8578
  -1.000   0.0929   0.00956   0.00331  -0.0364   0.7157   0.8833
  -0.750   0.1275   0.00965   0.00334  -0.0376   0.7090   0.9021
  -0.500   0.1634   0.00976   0.00334  -0.0390   0.7033   0.9172
  -0.250   0.1987   0.00986   0.00339  -0.0405   0.6968   0.9304
   0.000   0.2331   0.00998   0.00342  -0.0417   0.6908   0.9422
   0.250   0.2740   0.01008   0.00346  -0.0444   0.6848   0.9493
   0.500   0.3097   0.01018   0.00349  -0.0461   0.6786   0.9581
   0.750   0.3482   0.01026   0.00351  -0.0483   0.6730   0.9653
   1.000   0.3835   0.01032   0.00356  -0.0501   0.6664   0.9722
   1.250   0.4199   0.01037   0.00355  -0.0520   0.6608   0.9776
   1.500   0.4531   0.01042   0.00360  -0.0533   0.6541   0.9835
   1.750   0.4890   0.01043   0.00360  -0.0553   0.6481   0.9875
   2.000   0.5230   0.01046   0.00364  -0.0568   0.6414   0.9920
   2.250   0.5569   0.01049   0.00366  -0.0583   0.6343   0.9960
   2.500   0.5912   0.01051   0.00370  -0.0600   0.6261   0.9998
   2.750   0.6139   0.01056   0.00374  -0.0591   0.6182   1.0000
   3.000   0.6356   0.01060   0.00383  -0.0580   0.6084   1.0000
   3.250   0.6575   0.01066   0.00391  -0.0569   0.5989   1.0000
   3.500   0.6794   0.01074   0.00400  -0.0558   0.5895   1.0000
   3.750   0.7011   0.01081   0.00412  -0.0547   0.5786   1.0000
   4.000   0.7228   0.01090   0.00424  -0.0536   0.5670   1.0000
   4.250   0.7444   0.01099   0.00436  -0.0524   0.5542   1.0000
   4.500   0.7658   0.01110   0.00450  -0.0511   0.5403   1.0000
   4.750   0.7870   0.01123   0.00468  -0.0499   0.5251   1.0000
   5.000   0.8078   0.01138   0.00484  -0.0485   0.5077   1.0000
   5.250   0.8280   0.01156   0.00502  -0.0470   0.4849   1.0000
   5.500   0.8471   0.01179   0.00522  -0.0454   0.4563   1.0000
   5.750   0.8642   0.01213   0.00544  -0.0434   0.4161   1.0000
   6.000   0.8772   0.01271   0.00576  -0.0407   0.3567   1.0000
   6.250   0.8857   0.01361   0.00626  -0.0375   0.2840   1.0000
   6.500   0.8949   0.01455   0.00691  -0.0345   0.2220   1.0000
   6.750   0.9050   0.01545   0.00754  -0.0318   0.1712   1.0000
   7.000   0.9164   0.01627   0.00817  -0.0292   0.1320   1.0000
   7.250   0.9281   0.01709   0.00883  -0.0267   0.0984   1.0000
   7.500   0.9403   0.01788   0.00950  -0.0244   0.0733   1.0000
   7.750   0.9518   0.01871   0.01024  -0.0219   0.0532   1.0000
   8.000   0.9630   0.01954   0.01105  -0.0194   0.0399   1.0000
   8.250   0.9734   0.02041   0.01192  -0.0167   0.0329   1.0000
   8.500   0.9843   0.02119   0.01282  -0.0142   0.0287   1.0000
   8.750   0.9907   0.02211   0.01377  -0.0110   0.0256   1.0000
   9.000   0.9979   0.02302   0.01477  -0.0080   0.0235   1.0000
   9.250   1.0058   0.02397   0.01584  -0.0053   0.0223   1.0000
   9.500   1.0137   0.02498   0.01696  -0.0029   0.0207   1.0000
   9.750   1.0211   0.02611   0.01817  -0.0007   0.0192   1.0000
  10.000   1.0243   0.02761   0.01971   0.0017   0.0175   1.0000
  10.250   1.0295   0.02910   0.02130   0.0038   0.0166   1.0000
  10.500   1.0373   0.03049   0.02284   0.0055   0.0158   1.0000
  10.750   1.0448   0.03198   0.02448   0.0071   0.0148   1.0000
  11.000   1.0527   0.03342   0.02602   0.0084   0.0135   1.0000
  11.250   1.0593   0.03500   0.02768   0.0096   0.0125   1.0000
  11.500   1.0618   0.03711   0.02987   0.0110   0.0117   1.0000
  11.750   1.0665   0.03926   0.03214   0.0123   0.0112   1.0000
  12.000   1.0730   0.04120   0.03429   0.0134   0.0105   1.0000
  12.250   1.0781   0.04339   0.03666   0.0145   0.0102   1.0000
  12.500   1.0816   0.04581   0.03928   0.0155   0.0098   1.0000
  12.750   1.0826   0.04850   0.04217   0.0163   0.0093   1.0000
  13.000   1.0825   0.05130   0.04518   0.0168   0.0090   1.0000
  13.250   1.0803   0.05438   0.04845   0.0171   0.0087   1.0000
  13.500   1.0779   0.05733   0.05156   0.0170   0.0084   1.0000
  13.750   1.0731   0.06072   0.05510   0.0167   0.0081   1.0000
  14.000   1.0676   0.06429   0.05882   0.0160   0.0080   1.0000
  14.250   1.0616   0.06798   0.06265   0.0150   0.0077   1.0000
  14.500   1.0512   0.07261   0.06744   0.0137   0.0075   1.0000
  15.000   1.0254   0.08355   0.07877   0.0096   0.0074   1.0000
  15.250   1.0098   0.08996   0.08536   0.0065   0.0073   1.0000
  15.750   0.9793   0.10405   0.09982  -0.0011   0.0073   1.0000
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