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E230 (9.96%) (e230-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E230 (9.96%) (e230-il)
Reynolds number: 100,000
Max Cl/Cd: 32.24 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e230-il-100000-n5.txt
Download as CSV file: xf-e230-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E230  (9.96%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8311   0.09734   0.09263   0.0206   1.0000   0.0185
 -11.750  -0.8675   0.08356   0.07871   0.0102   1.0000   0.0179
 -11.500  -0.8975   0.07392   0.06887   0.0027   1.0000   0.0175
 -11.250  -0.9227   0.06700   0.06172  -0.0016   1.0000   0.0174
 -11.000  -0.9451   0.06163   0.05608  -0.0034   1.0000   0.0172
 -10.750  -0.9635   0.05739   0.05157  -0.0031   1.0000   0.0172
 -10.500  -0.9775   0.05386   0.04777  -0.0015   1.0000   0.0172
 -10.250  -0.9872   0.05070   0.04432   0.0009   1.0000   0.0172
 -10.000  -0.9904   0.04761   0.04090   0.0031   1.0000   0.0173
  -9.750  -0.9879   0.04466   0.03761   0.0049   1.0000   0.0174
  -9.500  -0.9810   0.04189   0.03449   0.0066   1.0000   0.0176
  -9.250  -0.9706   0.03929   0.03158   0.0082   1.0000   0.0179
  -9.000  -0.9570   0.03706   0.02907   0.0095   1.0000   0.0184
  -8.750  -0.9414   0.03503   0.02676   0.0108   1.0000   0.0194
  -8.500  -0.9237   0.03308   0.02450   0.0120   1.0000   0.0204
  -8.250  -0.9053   0.03116   0.02236   0.0131   1.0000   0.0212
  -8.000  -0.8876   0.02937   0.02049   0.0142   1.0000   0.0219
  -7.750  -0.8694   0.02784   0.01883   0.0154   1.0000   0.0227
  -7.500  -0.8509   0.02644   0.01730   0.0166   1.0000   0.0238
  -7.250  -0.8322   0.02513   0.01585   0.0179   1.0000   0.0252
  -7.000  -0.8129   0.02393   0.01446   0.0192   1.0000   0.0270
  -6.750  -0.7943   0.02267   0.01313   0.0205   1.0000   0.0300
  -6.500  -0.7740   0.02157   0.01195   0.0216   1.0000   0.0365
  -6.250  -0.7551   0.02024   0.01068   0.0229   1.0000   0.0515
  -6.000  -0.7355   0.01901   0.00965   0.0240   1.0000   0.0864
  -5.750  -0.7153   0.01798   0.00893   0.0249   1.0000   0.1381
  -5.500  -0.6955   0.01703   0.00837   0.0258   1.0000   0.2027
  -5.250  -0.6747   0.01629   0.00785   0.0267   1.0000   0.2565
  -5.000  -0.6526   0.01571   0.00738   0.0276   1.0000   0.2977
  -4.750  -0.6303   0.01520   0.00696   0.0285   1.0000   0.3382
  -4.500  -0.6082   0.01471   0.00658   0.0295   1.0000   0.3782
  -4.250  -0.5861   0.01426   0.00622   0.0305   1.0000   0.4177
  -4.000  -0.5641   0.01385   0.00593   0.0316   1.0000   0.4581
  -3.750  -0.5425   0.01348   0.00568   0.0328   1.0000   0.4985
  -3.500  -0.5212   0.01314   0.00547   0.0341   1.0000   0.5381
  -3.250  -0.5005   0.01284   0.00528   0.0355   1.0000   0.5777
  -3.000  -0.4803   0.01259   0.00515   0.0371   1.0000   0.6169
  -2.750  -0.4600   0.01239   0.00507   0.0386   1.0000   0.6555
  -2.500  -0.4242   0.01226   0.00503   0.0371   0.9888   0.6987
  -2.250  -0.3826   0.01220   0.00502   0.0347   0.9770   0.7401
  -2.000  -0.3393   0.01221   0.00507   0.0319   0.9657   0.7761
  -1.750  -0.2953   0.01226   0.00513   0.0291   0.9537   0.8066
  -1.500  -0.2521   0.01236   0.00520   0.0265   0.9404   0.8320
  -1.250  -0.2104   0.01247   0.00528   0.0242   0.9254   0.8531
  -1.000  -0.1734   0.01258   0.00534   0.0229   0.9085   0.8725
  -0.750  -0.1369   0.01270   0.00541   0.0218   0.8911   0.8884
  -0.500  -0.1025   0.01282   0.00548   0.0210   0.8732   0.9031
  -0.250  -0.0685   0.01292   0.00554   0.0203   0.8538   0.9167
   0.000  -0.0319   0.01303   0.00560   0.0191   0.8342   0.9273
   0.250   0.0027   0.01310   0.00562   0.0182   0.8144   0.9387
   0.500   0.0369   0.01316   0.00564   0.0173   0.7926   0.9501
   0.750   0.0704   0.01320   0.00564   0.0165   0.7708   0.9613
   1.000   0.1050   0.01323   0.00563   0.0153   0.7477   0.9721
   1.250   0.1420   0.01320   0.00556   0.0136   0.7237   0.9810
   1.500   0.1791   0.01316   0.00549   0.0118   0.6971   0.9896
   1.750   0.2164   0.01310   0.00540   0.0098   0.6690   0.9978
   2.000   0.2424   0.01309   0.00534   0.0101   0.6417   1.0000
   2.250   0.2642   0.01313   0.00532   0.0113   0.6144   1.0000
   2.500   0.2865   0.01319   0.00532   0.0124   0.5861   1.0000
   2.750   0.3091   0.01328   0.00537   0.0134   0.5566   1.0000
   3.000   0.3319   0.01340   0.00543   0.0143   0.5256   1.0000
   3.250   0.3550   0.01356   0.00553   0.0152   0.4929   1.0000
   3.500   0.3780   0.01375   0.00568   0.0161   0.4586   1.0000
   3.750   0.4011   0.01400   0.00585   0.0169   0.4235   1.0000
   4.000   0.4244   0.01427   0.00606   0.0177   0.3866   1.0000
   4.250   0.4475   0.01461   0.00631   0.0184   0.3480   1.0000
   4.500   0.4705   0.01501   0.00664   0.0191   0.3077   1.0000
   4.750   0.4934   0.01546   0.00700   0.0198   0.2669   1.0000
   5.000   0.5159   0.01600   0.00742   0.0204   0.2229   1.0000
   5.250   0.5377   0.01670   0.00788   0.0210   0.1712   1.0000
   5.500   0.5588   0.01755   0.00844   0.0215   0.1186   1.0000
   5.750   0.5802   0.01837   0.00913   0.0222   0.0829   1.0000
   6.000   0.6005   0.01946   0.01009   0.0231   0.0557   1.0000
   6.250   0.6203   0.02059   0.01118   0.0241   0.0421   1.0000
   6.500   0.6401   0.02160   0.01225   0.0251   0.0354   1.0000
   6.750   0.6588   0.02277   0.01353   0.0263   0.0324   1.0000
   7.000   0.6775   0.02389   0.01483   0.0276   0.0303   1.0000
   7.250   0.6955   0.02510   0.01614   0.0289   0.0287   1.0000
   7.500   0.7129   0.02638   0.01751   0.0302   0.0275   1.0000
   7.750   0.7294   0.02791   0.01909   0.0316   0.0266   1.0000
   8.000   0.7463   0.02956   0.02089   0.0330   0.0258   1.0000
   8.250   0.7633   0.03115   0.02275   0.0344   0.0246   1.0000
   8.500   0.7789   0.03288   0.02475   0.0357   0.0234   1.0000
   8.750   0.7929   0.03472   0.02683   0.0371   0.0225   1.0000
   9.000   0.8049   0.03689   0.02926   0.0386   0.0221   1.0000
   9.250   0.8141   0.03927   0.03191   0.0401   0.0218   1.0000
   9.500   0.8202   0.04181   0.03474   0.0417   0.0215   1.0000
   9.750   0.8223   0.04458   0.03781   0.0434   0.0214   1.0000
  10.000   0.8198   0.04752   0.04102   0.0450   0.0213   1.0000
  10.250   0.8116   0.05064   0.04440   0.0465   0.0212   1.0000
  10.500   0.7948   0.05380   0.04777   0.0482   0.0213   1.0000
  10.750   0.7752   0.05784   0.05202   0.0477   0.0214   1.0000
  11.000   0.7519   0.06338   0.05777   0.0447   0.0216   1.0000
  11.250   0.7161   0.07276   0.06739   0.0373   0.0220   1.0000
  11.500   0.6690   0.08808   0.08283   0.0257   0.0229   1.0000
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