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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 200,000
Max Cl/Cd: 103.48 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e71-il-200000-n5.txt
Download as CSV file: xf-e71-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E71  (5.15%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3794   0.10452   0.10112  -0.0218   1.0000   0.0134
  -7.500  -0.3826   0.10235   0.09900  -0.0206   1.0000   0.0134
  -7.250  -0.3874   0.10034   0.09704  -0.0191   1.0000   0.0134
  -7.000  -0.3840   0.09755   0.09428  -0.0200   0.9986   0.0134
  -6.750  -0.3713   0.09147   0.08825  -0.0250   0.9953   0.0138
  -6.500  -0.3571   0.08709   0.08386  -0.0278   0.9925   0.0144
  -6.250  -0.3421   0.08403   0.08081  -0.0293   0.9895   0.0159
  -6.000  -0.3205   0.08035   0.07712  -0.0346   0.9856   0.0182
  -5.750  -0.2742   0.07534   0.07207  -0.0514   0.9807   0.0226
  -5.500  -0.2446   0.07050   0.06719  -0.0597   0.9758   0.0228
  -5.250  -0.2216   0.06359   0.06027  -0.0671   0.9724   0.0236
  -5.000  -0.2002   0.06038   0.05705  -0.0694   0.9703   0.0252
  -4.750  -0.1741   0.05676   0.05338  -0.0743   0.9657   0.0270
  -3.750   0.0249   0.03312   0.02879  -0.1162   0.9584   0.0307
  -3.500   0.0852   0.02589   0.02075  -0.1253   0.9589   0.0216
  -3.250   0.1303   0.02237   0.01664  -0.1304   0.9586   0.0203
  -3.000   0.1727   0.01981   0.01354  -0.1340   0.9582   0.0193
  -2.750   0.2124   0.01798   0.01125  -0.1367   0.9575   0.0186
  -2.500   0.2461   0.01666   0.00962  -0.1379   0.9549   0.0182
  -2.250   0.2789   0.01564   0.00840  -0.1389   0.9519   0.0181
  -2.000   0.3135   0.01479   0.00742  -0.1404   0.9495   0.0183
  -1.750   0.3493   0.01412   0.00662  -0.1421   0.9474   0.0189
  -1.500   0.3861   0.01360   0.00599  -0.1440   0.9455   0.0203
  -1.250   0.4173   0.01326   0.00555  -0.1447   0.9411   0.0223
  -1.000   0.4501   0.01292   0.00521  -0.1457   0.9368   0.0326
  -0.750   0.4864   0.01251   0.00490  -0.1475   0.9338   0.0717
  -0.500   0.5253   0.01181   0.00480  -0.1503   0.9318   0.2627
  -0.250   0.5543   0.01149   0.00475  -0.1506   0.9245   0.3715
   0.000   0.5904   0.01095   0.00469  -0.1524   0.9208   0.5445
   0.500   0.6409   0.00982   0.00435  -0.1502   0.9077   1.0000
   0.750   0.6727   0.00972   0.00421  -0.1508   0.8995   1.0000
   1.000   0.7106   0.00954   0.00399  -0.1526   0.8928   1.0000
   1.250   0.7434   0.00945   0.00391  -0.1534   0.8821   1.0000
   1.500   0.7786   0.00933   0.00377  -0.1546   0.8705   1.0000
   1.750   0.8153   0.00919   0.00363  -0.1562   0.8564   1.0000
   2.000   0.8526   0.00908   0.00351  -0.1578   0.8396   1.0000
   2.250   0.8867   0.00906   0.00352  -0.1588   0.8179   1.0000
   2.500   0.9204   0.00908   0.00349  -0.1597   0.7893   1.0000
   2.750   0.9512   0.00921   0.00353  -0.1599   0.7532   1.0000
   3.000   0.9789   0.00946   0.00363  -0.1595   0.7081   1.0000
   3.250   1.0032   0.00987   0.00380  -0.1584   0.6504   1.0000
   3.500   1.0243   0.01045   0.00407  -0.1567   0.5810   1.0000
   3.750   1.0357   0.01177   0.00462  -0.1534   0.4368   1.0000
   4.000   1.0469   0.01344   0.00532  -0.1507   0.2743   1.0000
   4.250   1.0672   0.01438   0.00589  -0.1495   0.2014   1.0000
   4.500   1.0885   0.01525   0.00649  -0.1485   0.1425   1.0000
   4.750   1.1086   0.01635   0.00723  -0.1474   0.0779   1.0000
   5.000   1.1282   0.01758   0.00813  -0.1460   0.0246   1.0000
   5.250   1.1494   0.01861   0.00907  -0.1448   0.0107   1.0000
   5.500   1.1716   0.01952   0.01012  -0.1436   0.0089   1.0000
   5.750   1.1939   0.02041   0.01120  -0.1425   0.0084   1.0000
   6.000   1.2153   0.02143   0.01252  -0.1412   0.0081   1.0000
   6.250   1.2353   0.02265   0.01393  -0.1396   0.0078   1.0000
   6.500   1.2544   0.02407   0.01553  -0.1380   0.0076   1.0000
   6.750   1.2733   0.02570   0.01734  -0.1363   0.0075   1.0000
   7.000   1.2926   0.02758   0.01941  -0.1346   0.0074   1.0000
   7.250   1.3128   0.02974   0.02180  -0.1331   0.0073   1.0000
   7.500   1.3333   0.03225   0.02460  -0.1316   0.0073   1.0000
   7.750   1.3527   0.03471   0.02740  -0.1300   0.0068   1.0000
   8.000   1.3701   0.03708   0.03012  -0.1283   0.0061   1.0000
   8.250   1.3849   0.03961   0.03301  -0.1263   0.0055   1.0000
   8.500   1.3958   0.04312   0.03706  -0.1237   0.0053   1.0000
   8.750   1.4021   0.04706   0.04149  -0.1207   0.0053   1.0000
   9.000   1.4031   0.05128   0.04619  -0.1172   0.0053   1.0000
   9.250   1.3978   0.05585   0.05122  -0.1133   0.0052   1.0000
   9.500   1.3860   0.06025   0.05600  -0.1089   0.0053   1.0000
   9.750   1.3685   0.06437   0.06043  -0.1043   0.0053   1.0000
  10.000   1.3490   0.06886   0.06520  -0.1007   0.0053   1.0000
  10.250   1.3281   0.07384   0.07044  -0.0983   0.0054   1.0000
  10.500   1.3069   0.07936   0.07619  -0.0976   0.0054   1.0000
  10.750   1.2844   0.08576   0.08280  -0.0986   0.0055   1.0000
  11.000   1.2622   0.09314   0.09037  -0.1017   0.0055   1.0000
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