Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E471 (6.25%) (e471-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 50,000
Max Cl/Cd: 46.81 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e471-il-50000-n5.txt
Download as CSV file: xf-e471-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3608   0.11157   0.10497  -0.0295   1.0000   0.0903
  -7.750  -0.3734   0.11116   0.10470  -0.0288   1.0000   0.0913
  -7.500  -0.3875   0.11080   0.10449  -0.0279   1.0000   0.0917
  -7.250  -0.3905   0.10824   0.10205  -0.0275   1.0000   0.0923
  -7.000  -0.3760   0.10277   0.09646  -0.0241   1.0000   0.0953
  -6.750  -0.3776   0.10048   0.09424  -0.0226   1.0000   0.0977
  -6.500  -0.3806   0.09839   0.09223  -0.0220   1.0000   0.1004
  -6.250  -0.3860   0.09683   0.09077  -0.0236   1.0000   0.1041
  -6.000  -0.3872   0.09545   0.08948  -0.0304   1.0000   0.1056
  -5.750  -0.3842   0.09125   0.08534  -0.0260   1.0000   0.1071
  -5.500  -0.3802   0.08816   0.08230  -0.0241   1.0000   0.1095
  -5.250  -0.3752   0.08535   0.07951  -0.0245   1.0000   0.1128
  -4.750  -0.3537   0.07864   0.07283  -0.0329   1.0000   0.1213
  -4.500  -0.3436   0.07537   0.06957  -0.0332   1.0000   0.1234
  -4.250  -0.2977   0.06645   0.06031  -0.0469   1.0000   0.0628
  -4.000  -0.2570   0.05950   0.05310  -0.0572   1.0000   0.0531
  -3.750  -0.2173   0.05427   0.04754  -0.0648   1.0000   0.0507
  -3.500  -0.1872   0.05026   0.04338  -0.0695   1.0000   0.0538
  -3.250  -0.1268   0.04404   0.03634  -0.0806   1.0000   0.0519
  -3.000  -0.0880   0.04029   0.03217  -0.0852   1.0000   0.0507
  -2.750  -0.0463   0.03674   0.02810  -0.0899   1.0000   0.0500
  -2.500  -0.0054   0.03379   0.02454  -0.0938   1.0000   0.0496
  -2.250   0.0384   0.03132   0.02134  -0.0976   0.9979   0.0496
  -2.000   0.0782   0.02952   0.01898  -0.1002   0.9954   0.0500
  -1.750   0.1154   0.02822   0.01720  -0.1021   0.9925   0.0511
  -1.500   0.1507   0.02715   0.01587  -0.1037   0.9891   0.0530
  -1.250   0.1867   0.02646   0.01494  -0.1055   0.9855   0.0573
  -1.000   0.2246   0.02602   0.01430  -0.1078   0.9823   0.0706
  -0.750   0.2606   0.02539   0.01366  -0.1098   0.9779   0.1078
  -0.500   0.2954   0.02326   0.01381  -0.1119   0.9766   0.6238
  -0.250   0.3173   0.02286   0.01355  -0.1103   0.9684   1.0000
   0.000   0.3496   0.02326   0.01351  -0.1116   0.9615   1.0000
   0.250   0.3862   0.02373   0.01359  -0.1137   0.9561   1.0000
   0.500   0.4169   0.02411   0.01371  -0.1148   0.9483   1.0000
   0.750   0.4516   0.02455   0.01392  -0.1166   0.9418   1.0000
   1.000   0.4837   0.02494   0.01415  -0.1178   0.9340   1.0000
   1.250   0.5156   0.02533   0.01441  -0.1191   0.9262   1.0000
   1.500   0.5512   0.02571   0.01468  -0.1209   0.9190   1.0000
   1.750   0.5809   0.02607   0.01499  -0.1216   0.9096   1.0000
   2.000   0.6149   0.02641   0.01529  -0.1230   0.9014   1.0000
   2.250   0.6496   0.02669   0.01560  -0.1245   0.8926   1.0000
   2.500   0.6796   0.02699   0.01593  -0.1251   0.8819   1.0000
   2.750   0.7116   0.02724   0.01624  -0.1260   0.8715   1.0000
   3.000   0.7466   0.02738   0.01649  -0.1272   0.8615   1.0000
   3.250   0.7839   0.02740   0.01669  -0.1286   0.8513   1.0000
   3.500   0.8161   0.02744   0.01688  -0.1291   0.8385   1.0000
   3.750   0.8497   0.02736   0.01699  -0.1297   0.8253   1.0000
   4.000   0.8845   0.02713   0.01697  -0.1302   0.8115   1.0000
   4.250   0.9195   0.02679   0.01697  -0.1304   0.7961   1.0000
   4.500   0.9482   0.02660   0.01701  -0.1297   0.7766   1.0000
   4.750   0.9857   0.02597   0.01668  -0.1299   0.7576   1.0000
   5.000   1.0146   0.02559   0.01659  -0.1287   0.7328   1.0000
   5.250   1.0459   0.02503   0.01631  -0.1276   0.7033   1.0000
   5.500   1.0736   0.02465   0.01631  -0.1259   0.6641   1.0000
   5.750   1.1028   0.02426   0.01608  -0.1243   0.6103   1.0000
   6.000   1.1319   0.02418   0.01589  -0.1225   0.5303   1.0000
   6.250   1.1516   0.02499   0.01627  -0.1198   0.4358   1.0000
   6.500   1.1623   0.02649   0.01731  -0.1167   0.3488   1.0000
   6.750   1.1700   0.02831   0.01871  -0.1136   0.2696   1.0000
   7.000   1.1776   0.03039   0.02037  -0.1108   0.1991   1.0000
   7.250   1.1848   0.03286   0.02236  -0.1083   0.1322   1.0000
   7.500   1.1936   0.03553   0.02442  -0.1063   0.0696   1.0000
   7.750   1.2062   0.03804   0.02682  -0.1044   0.0462   1.0000
   8.000   1.2200   0.04053   0.02964  -0.1022   0.0384   1.0000
   8.250   1.2364   0.04300   0.03233  -0.1005   0.0340   1.0000
   8.500   1.2558   0.04612   0.03555  -0.0993   0.0311   1.0000
   8.750   1.2851   0.04949   0.03942  -0.0988   0.0293   1.0000
   9.000   1.3074   0.05318   0.04363  -0.0978   0.0278   1.0000
   9.250   1.3205   0.05682   0.04778  -0.0960   0.0261   1.0000
   9.500   1.3269   0.06035   0.05174  -0.0938   0.0247   1.0000
   9.750   1.3267   0.06373   0.05550  -0.0911   0.0236   1.0000
  10.000   1.3221   0.06720   0.05931  -0.0882   0.0228   1.0000
  10.250   1.3140   0.07084   0.06328  -0.0855   0.0223   1.0000
  10.500   1.3028   0.07484   0.06761  -0.0831   0.0221   1.0000
  10.750   1.2888   0.07921   0.07229  -0.0813   0.0220   1.0000
  11.000   1.2723   0.08406   0.07745  -0.0802   0.0220   1.0000
  11.250   1.2535   0.08951   0.08319  -0.0803   0.0221   1.0000
  11.500   1.2327   0.09575   0.08971  -0.0816   0.0224   1.0000
  11.750   1.2096   0.10317   0.09739  -0.0846   0.0229   1.0000
  12.000   1.1819   0.11279   0.10724  -0.0902   0.0241   1.0000
<< Back to E471 (6.25%) (e471-il)

Polar data table (+)

Polar graphs


<< Back to E471 (6.25%) (e471-il)