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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 100,000
Max Cl/Cd: 74.01 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e71-il-100000-n5.txt
Download as CSV file: xf-e71-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3750   0.09795   0.09332  -0.0198   1.0000   0.0395
  -6.750  -0.3801   0.09616   0.09160  -0.0182   1.0000   0.0407
  -6.500  -0.3836   0.09415   0.08966  -0.0173   1.0000   0.0419
  -6.250  -0.3843   0.09187   0.08744  -0.0176   1.0000   0.0433
  -6.000  -0.3827   0.08958   0.08522  -0.0193   1.0000   0.0449
  -5.750  -0.3734   0.08723   0.08292  -0.0261   1.0000   0.0463
  -5.500  -0.3562   0.08390   0.07958  -0.0337   1.0000   0.0468
  -5.250  -0.3363   0.07991   0.07555  -0.0402   1.0000   0.0470
  -5.000  -0.3286   0.07456   0.07027  -0.0394   0.9982   0.0479
  -4.750  -0.3119   0.07063   0.06634  -0.0398   0.9952   0.0494
  -4.500  -0.2841   0.06647   0.06213  -0.0448   0.9919   0.0513
  -4.250  -0.2473   0.06169   0.05726  -0.0530   0.9882   0.0534
  -4.000  -0.1906   0.05528   0.05065  -0.0681   0.9855   0.0629
  -3.750  -0.1291   0.04956   0.04457  -0.0823   0.9837   0.0748
  -3.500  -0.0632   0.03957   0.03393  -0.0933   0.9841   0.0336
  -3.250  -0.0175   0.03476   0.02882  -0.1004   0.9836   0.0315
  -3.000   0.0336   0.03039   0.02389  -0.1074   0.9836   0.0297
  -2.750   0.0828   0.02684   0.01958  -0.1130   0.9837   0.0282
  -2.500   0.1280   0.02419   0.01626  -0.1170   0.9834   0.0272
  -2.250   0.1693   0.02235   0.01390  -0.1198   0.9825   0.0268
  -2.000   0.2060   0.02103   0.01226  -0.1217   0.9803   0.0271
  -1.750   0.2415   0.02004   0.01106  -0.1233   0.9774   0.0278
  -1.500   0.2776   0.01931   0.01018  -0.1251   0.9744   0.0296
  -1.250   0.3144   0.01882   0.00955  -0.1272   0.9715   0.0369
  -1.000   0.3508   0.01843   0.00905  -0.1290   0.9682   0.0451
  -0.750   0.3854   0.01795   0.00857  -0.1305   0.9635   0.0639
  -0.500   0.4243   0.01700   0.00858  -0.1336   0.9610   0.3504
  -0.250   0.4601   0.01644   0.00864  -0.1353   0.9579   0.5965
   0.000   0.4761   0.01567   0.00845  -0.1322   0.9485   1.0000
   0.250   0.5127   0.01577   0.00836  -0.1340   0.9434   1.0000
   0.500   0.5444   0.01583   0.00830  -0.1348   0.9354   1.0000
   0.750   0.5792   0.01587   0.00824  -0.1362   0.9288   1.0000
   1.000   0.6136   0.01588   0.00818  -0.1375   0.9213   1.0000
   1.250   0.6463   0.01588   0.00814  -0.1384   0.9129   1.0000
   1.500   0.6845   0.01576   0.00802  -0.1402   0.9063   1.0000
   2.000   0.7503   0.01553   0.00787  -0.1416   0.8859   1.0000
   2.250   0.7867   0.01528   0.00769  -0.1428   0.8763   1.0000
   2.500   0.8234   0.01502   0.00750  -0.1440   0.8648   1.0000
   2.750   0.8566   0.01483   0.00749  -0.1445   0.8493   1.0000
   3.000   0.8909   0.01464   0.00740  -0.1452   0.8316   1.0000
   3.250   0.9290   0.01437   0.00724  -0.1465   0.8118   1.0000
   3.500   0.9642   0.01420   0.00717  -0.1472   0.7843   1.0000
   3.750   0.9996   0.01408   0.00711  -0.1478   0.7467   1.0000
   4.000   1.0348   0.01409   0.00720  -0.1484   0.6933   1.0000
   4.250   1.0658   0.01440   0.00730  -0.1481   0.6173   1.0000
   4.500   1.0892   0.01513   0.00765  -0.1466   0.5235   1.0000
   4.750   1.1019   0.01669   0.00828  -0.1435   0.3737   1.0000
   5.000   1.1145   0.01847   0.00916  -0.1412   0.2352   1.0000
   5.250   1.1329   0.01980   0.01008  -0.1398   0.1569   1.0000
   5.500   1.1487   0.02165   0.01125  -0.1381   0.0639   1.0000
   5.750   1.1665   0.02337   0.01277  -0.1363   0.0278   1.0000
   6.000   1.1854   0.02500   0.01466  -0.1344   0.0212   1.0000
   6.250   1.2050   0.02632   0.01618  -0.1329   0.0174   1.0000
   6.500   1.2225   0.02798   0.01797  -0.1312   0.0145   1.0000
   6.750   1.2406   0.02962   0.01987  -0.1294   0.0134   1.0000
   7.000   1.2583   0.03157   0.02206  -0.1275   0.0128   1.0000
   7.250   1.2771   0.03381   0.02453  -0.1258   0.0123   1.0000
   7.500   1.2973   0.03637   0.02737  -0.1243   0.0120   1.0000
   7.750   1.3175   0.03929   0.03063  -0.1229   0.0117   1.0000
   8.000   1.3357   0.04260   0.03437  -0.1212   0.0116   1.0000
   8.250   1.3502   0.04630   0.03858  -0.1190   0.0115   1.0000
   8.500   1.3599   0.05032   0.04313  -0.1164   0.0115   1.0000
   8.750   1.3642   0.05458   0.04793  -0.1133   0.0115   1.0000
   9.000   1.3631   0.05902   0.05287  -0.1100   0.0116   1.0000
   9.250   1.3564   0.06357   0.05798  -0.1064   0.0117   1.0000
   9.500   1.3438   0.06782   0.06261  -0.1026   0.0118   1.0000
   9.750   1.3266   0.07190   0.06700  -0.0988   0.0119   1.0000
  10.000   1.3075   0.07636   0.07174  -0.0960   0.0119   1.0000
  10.250   1.2870   0.08135   0.07698  -0.0945   0.0120   1.0000
  10.500   1.2664   0.08688   0.08263  -0.0946   0.0121   1.0000
  10.750   1.2450   0.09328   0.08924  -0.0965   0.0122   1.0000
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