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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 200,000
Max Cl/Cd: 101.11 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e471-il-200000-n5.txt
Download as CSV file: xf-e471-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E471  (6.25%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2357   0.08557   0.08233  -0.0435   0.9861   0.0197
  -7.750  -0.2252   0.08157   0.07833  -0.0462   0.9838   0.0206
  -7.500  -0.3246   0.09361   0.09030  -0.0375   0.9907   0.0184
  -7.250  -0.3114   0.09022   0.08687  -0.0402   0.9870   0.0191
  -7.000  -0.2966   0.08678   0.08343  -0.0440   0.9834   0.0197
  -6.750  -0.2848   0.08341   0.08007  -0.0472   0.9776   0.0204
  -6.500  -0.2659   0.07938   0.07604  -0.0525   0.9726   0.0213
  -6.250  -0.2431   0.07501   0.07166  -0.0593   0.9687   0.0225
  -6.000  -0.2259   0.07104   0.06769  -0.0646   0.9615   0.0237
  -5.000  -0.0768   0.05011   0.04633  -0.1065   0.9447   0.0381
  -4.500  -0.0175   0.03720   0.03309  -0.1178   0.9359   0.0230
  -4.250   0.0401   0.02773   0.02281  -0.1290   0.9349   0.0191
  -4.000   0.0854   0.02317   0.01752  -0.1342   0.9338   0.0181
  -3.750   0.1254   0.02043   0.01423  -0.1376   0.9327   0.0182
  -3.500   0.1636   0.01845   0.01182  -0.1403   0.9316   0.0188
  -3.250   0.1937   0.01734   0.01044  -0.1411   0.9277   0.0203
  -3.000   0.2249   0.01659   0.00950  -0.1420   0.9242   0.0229
  -2.750   0.2595   0.01547   0.00818  -0.1434   0.9220   0.0228
  -2.500   0.2947   0.01455   0.00712  -0.1449   0.9203   0.0227
  -2.250   0.3308   0.01379   0.00627  -0.1467   0.9189   0.0226
  -2.000   0.3629   0.01328   0.00564  -0.1476   0.9155   0.0227
  -1.750   0.3933   0.01291   0.00517  -0.1482   0.9111   0.0231
  -1.500   0.4275   0.01257   0.00472  -0.1494   0.9083   0.0239
  -1.250   0.4626   0.01227   0.00433  -0.1509   0.9060   0.0258
  -1.000   0.4949   0.01193   0.00408  -0.1518   0.9022   0.0539
  -0.750   0.5261   0.01142   0.00401  -0.1529   0.8973   0.1937
  -0.500   0.5610   0.01056   0.00411  -0.1550   0.8941   0.4921
  -0.250   0.5785   0.00958   0.00414  -0.1520   0.8892   0.8649
   0.000   0.6062   0.00943   0.00396  -0.1516   0.8822   1.0000
   0.250   0.6414   0.00934   0.00377  -0.1530   0.8780   1.0000
   0.500   0.6693   0.00937   0.00374  -0.1529   0.8694   1.0000
   0.750   0.7028   0.00931   0.00361  -0.1539   0.8632   1.0000
   1.000   0.7319   0.00932   0.00359  -0.1540   0.8540   1.0000
   1.250   0.7617   0.00932   0.00355  -0.1542   0.8445   1.0000
   1.500   0.7925   0.00931   0.00350  -0.1547   0.8348   1.0000
   1.750   0.8228   0.00931   0.00348  -0.1549   0.8241   1.0000
   2.000   0.8511   0.00936   0.00354  -0.1548   0.8111   1.0000
   2.500   0.9065   0.00948   0.00364  -0.1543   0.7810   1.0000
   2.750   0.9335   0.00957   0.00372  -0.1540   0.7632   1.0000
   3.000   0.9607   0.00967   0.00380  -0.1536   0.7425   1.0000
   3.250   0.9868   0.00982   0.00395  -0.1530   0.7167   1.0000
   3.500   1.0121   0.01001   0.00408  -0.1522   0.6846   1.0000
   3.750   1.0362   0.01029   0.00424  -0.1511   0.6431   1.0000
   4.000   1.0580   0.01071   0.00445  -0.1497   0.5890   1.0000
   4.250   1.0770   0.01134   0.00477  -0.1478   0.5229   1.0000
   4.500   1.0917   0.01229   0.00526  -0.1453   0.4354   1.0000
   4.750   1.1013   0.01376   0.00597  -0.1422   0.3092   1.0000
   5.000   1.1155   0.01506   0.00676  -0.1401   0.2118   1.0000
   5.250   1.1347   0.01595   0.00740  -0.1388   0.1594   1.0000
   5.500   1.1540   0.01687   0.00809  -0.1375   0.1122   1.0000
   5.750   1.1712   0.01805   0.00893  -0.1360   0.0576   1.0000
   6.000   1.1876   0.01940   0.00997  -0.1342   0.0166   1.0000
   6.250   1.2076   0.02032   0.01093  -0.1328   0.0112   1.0000
   6.500   1.2277   0.02122   0.01195  -0.1314   0.0096   1.0000
   6.750   1.2468   0.02225   0.01313  -0.1299   0.0086   1.0000
   7.000   1.2640   0.02353   0.01469  -0.1280   0.0080   1.0000
   7.250   1.2793   0.02498   0.01632  -0.1259   0.0077   1.0000
   7.500   1.2949   0.02641   0.01791  -0.1239   0.0076   1.0000
   7.750   1.3101   0.02801   0.01969  -0.1218   0.0075   1.0000
   8.000   1.3259   0.02978   0.02163  -0.1199   0.0073   1.0000
   8.250   1.3431   0.03144   0.02348  -0.1183   0.0069   1.0000
   8.500   1.3601   0.03310   0.02536  -0.1167   0.0063   1.0000
   8.750   1.3763   0.03503   0.02752  -0.1150   0.0057   1.0000
   9.000   1.3914   0.03751   0.03030  -0.1131   0.0056   1.0000
   9.250   1.4038   0.04028   0.03342  -0.1110   0.0054   1.0000
   9.500   1.4120   0.04323   0.03680  -0.1083   0.0053   1.0000
   9.750   1.4148   0.04638   0.04033  -0.1050   0.0052   1.0000
  10.000   1.4125   0.04968   0.04400  -0.1013   0.0052   1.0000
  10.250   1.4059   0.05318   0.04786  -0.0975   0.0052   1.0000
  10.500   1.3955   0.05694   0.05197  -0.0938   0.0052   1.0000
  10.750   1.3820   0.06105   0.05642  -0.0906   0.0052   1.0000
  11.000   1.3661   0.06553   0.06122  -0.0881   0.0052   1.0000
  11.250   1.3479   0.07054   0.06652  -0.0866   0.0052   1.0000
  11.500   1.3287   0.07602   0.07226  -0.0860   0.0052   1.0000
  11.750   1.3087   0.08207   0.07856  -0.0868   0.0053   1.0000
  12.000   1.2880   0.08883   0.08554  -0.0888   0.0053   1.0000
  12.250   1.2667   0.09656   0.09348  -0.0924   0.0054   1.0000
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