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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 100,000
Max Cl/Cd: 71.98 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e471-il-100000-n5.txt
Download as CSV file: xf-e471-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3792   0.11129   0.10670  -0.0297   1.0000   0.0381
  -7.750  -0.3881   0.10993   0.10543  -0.0281   1.0000   0.0382
  -7.500  -0.3949   0.10823   0.10381  -0.0273   1.0000   0.0383
  -7.250  -0.3978   0.10533   0.10101  -0.0270   1.0000   0.0384
  -7.000  -0.3882   0.09909   0.09473  -0.0220   1.0000   0.0401
  -6.750  -0.3908   0.09684   0.09247  -0.0199   1.0000   0.0409
  -6.500  -0.3865   0.09408   0.08974  -0.0203   0.9987   0.0422
  -6.250  -0.3674   0.09011   0.08577  -0.0252   0.9943   0.0442
  -6.000  -0.3481   0.08608   0.08173  -0.0309   0.9888   0.0464
  -5.750  -0.2997   0.08063   0.07619  -0.0534   0.9810   0.0513
  -5.500  -0.2901   0.07567   0.07128  -0.0535   0.9767   0.0529
  -5.250  -0.2766   0.07266   0.06827  -0.0522   0.9732   0.0558
  -5.000  -0.2456   0.06807   0.06362  -0.0596   0.9697   0.0584
  -4.750  -0.2177   0.06351   0.05898  -0.0667   0.9637   0.0604
  -4.500  -0.1481   0.05173   0.04675  -0.0880   0.9603   0.0393
  -4.250  -0.1198   0.04825   0.04319  -0.0910   0.9577   0.0341
  -4.000  -0.0690   0.04125   0.03579  -0.1013   0.9556   0.0306
  -3.750  -0.0082   0.03328   0.02685  -0.1121   0.9548   0.0276
  -3.500   0.0329   0.02980   0.02275  -0.1164   0.9523   0.0274
  -3.250   0.0671   0.02805   0.02083  -0.1194   0.9494   0.0310
  -3.000   0.1074   0.02583   0.01806  -0.1226   0.9475   0.0329
  -2.750   0.1475   0.02374   0.01537  -0.1252   0.9459   0.0325
  -2.500   0.1856   0.02224   0.01347  -0.1273   0.9443   0.0324
  -2.250   0.2159   0.02120   0.01223  -0.1279   0.9402   0.0326
  -2.000   0.2487   0.02035   0.01122  -0.1290   0.9366   0.0331
  -1.750   0.2839   0.01967   0.01040  -0.1305   0.9337   0.0342
  -1.500   0.3206   0.01914   0.00967  -0.1324   0.9313   0.0361
  -1.250   0.3488   0.01880   0.00921  -0.1326   0.9258   0.0401
  -1.000   0.3829   0.01834   0.00879  -0.1339   0.9220   0.0641
  -0.750   0.4207   0.01730   0.00883  -0.1368   0.9198   0.3629
  -0.500   0.4400   0.01607   0.00896  -0.1344   0.9160   0.8147
  -0.250   0.4656   0.01595   0.00874  -0.1338   0.9088   1.0000
   0.000   0.5023   0.01598   0.00857  -0.1355   0.9054   1.0000
   0.250   0.5298   0.01612   0.00857  -0.1355   0.8982   1.0000
   0.500   0.5648   0.01613   0.00845  -0.1369   0.8937   1.0000
   0.750   0.5970   0.01617   0.00839  -0.1377   0.8881   1.0000
   1.000   0.6286   0.01620   0.00835  -0.1384   0.8817   1.0000
   1.250   0.6675   0.01606   0.00817  -0.1404   0.8781   1.0000
   1.500   0.6944   0.01614   0.00825  -0.1401   0.8690   1.0000
   1.750   0.7340   0.01596   0.00806  -0.1421   0.8646   1.0000
   2.000   0.7616   0.01599   0.00811  -0.1419   0.8547   1.0000
   2.250   0.7940   0.01589   0.00805  -0.1424   0.8463   1.0000
   2.500   0.8301   0.01567   0.00793  -0.1435   0.8383   1.0000
   2.750   0.8596   0.01560   0.00792  -0.1435   0.8267   1.0000
   3.000   0.8904   0.01548   0.00788  -0.1436   0.8142   1.0000
   3.250   0.9215   0.01534   0.00783  -0.1436   0.8003   1.0000
   3.500   0.9531   0.01519   0.00784  -0.1438   0.7847   1.0000
   3.750   0.9811   0.01515   0.00790  -0.1433   0.7651   1.0000
   4.000   1.0121   0.01503   0.00787  -0.1432   0.7428   1.0000
   4.250   1.0395   0.01502   0.00795  -0.1425   0.7140   1.0000
   4.500   1.0672   0.01505   0.00801  -0.1418   0.6767   1.0000
   4.750   1.0941   0.01520   0.00811  -0.1408   0.6253   1.0000
   5.000   1.1184   0.01560   0.00837  -0.1395   0.5542   1.0000
   5.250   1.1373   0.01641   0.00879  -0.1373   0.4708   1.0000
   5.500   1.1519   0.01754   0.00947  -0.1348   0.3832   1.0000
   5.750   1.1621   0.01912   0.01036  -0.1319   0.2750   1.0000
   6.000   1.1743   0.02073   0.01136  -0.1297   0.1824   1.0000
   6.250   1.1887   0.02227   0.01242  -0.1279   0.1103   1.0000
   6.500   1.2028   0.02395   0.01369  -0.1259   0.0526   1.0000
   6.750   1.2171   0.02576   0.01537  -0.1236   0.0280   1.0000
   7.000   1.2318   0.02747   0.01717  -0.1214   0.0210   1.0000
   7.250   1.2480   0.02887   0.01887  -0.1195   0.0172   1.0000
   7.500   1.2636   0.03032   0.02049  -0.1176   0.0149   1.0000
   7.750   1.2765   0.03211   0.02246  -0.1154   0.0139   1.0000
   8.000   1.2877   0.03433   0.02484  -0.1129   0.0133   1.0000
   8.250   1.3026   0.03645   0.02718  -0.1110   0.0129   1.0000
   8.500   1.3196   0.03887   0.02986  -0.1093   0.0126   1.0000
   8.750   1.3377   0.04164   0.03294  -0.1078   0.0123   1.0000
   9.000   1.3545   0.04477   0.03645  -0.1063   0.0121   1.0000
   9.250   1.3674   0.04823   0.04034  -0.1043   0.0119   1.0000
   9.500   1.3746   0.05182   0.04438  -0.1017   0.0118   1.0000
   9.750   1.3750   0.05548   0.04848  -0.0985   0.0118   1.0000
  10.000   1.3695   0.05910   0.05251  -0.0948   0.0118   1.0000
  10.250   1.3600   0.06280   0.05658  -0.0912   0.0118   1.0000
  10.500   1.3473   0.06673   0.06085  -0.0880   0.0118   1.0000
  10.750   1.3323   0.07095   0.06540  -0.0854   0.0118   1.0000
  11.000   1.3155   0.07554   0.07029  -0.0837   0.0118   1.0000
  11.250   1.2968   0.08067   0.07569  -0.0830   0.0118   1.0000
  11.500   1.2775   0.08626   0.08153  -0.0834   0.0118   1.0000
  11.750   1.2579   0.09243   0.08794  -0.0851   0.0119   1.0000
  12.000   1.2382   0.09929   0.09499  -0.0880   0.0121   1.0000
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