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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 100,000
Max Cl/Cd: 61.17 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e392-il-100000.txt
Download as CSV file: xf-e392-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3175   0.10100   0.09622  -0.0367   1.0000   0.0855
  -8.500  -0.3258   0.09914   0.09447  -0.0391   1.0000   0.0883
  -8.250  -0.3441   0.09800   0.09351  -0.0417   1.0000   0.0892
  -8.000  -0.3271   0.09276   0.08827  -0.0390   1.0000   0.0921
  -7.750  -0.3199   0.09011   0.08566  -0.0374   1.0000   0.0953
  -7.500  -0.3247   0.08801   0.08367  -0.0366   1.0000   0.0983
  -7.250  -0.3407   0.08669   0.08251  -0.0350   1.0000   0.1004
  -7.000  -0.3664   0.08610   0.08210  -0.0325   1.0000   0.1017
  -6.750  -0.3921   0.08566   0.08182  -0.0299   1.0000   0.1021
  -6.500  -0.4162   0.08492   0.08118  -0.0293   1.0000   0.1026
  -6.250  -0.3978   0.07936   0.07563  -0.0355   0.9941   0.1058
  -6.000  -0.3612   0.07381   0.06994  -0.0483   0.9845   0.1170
  -5.750  -0.3372   0.06888   0.06502  -0.0513   0.9763   0.1213
  -5.500  -0.3037   0.06294   0.05889  -0.0628   0.9661   0.1343
  -5.250  -0.2679   0.05813   0.05390  -0.0707   0.9584   0.1485
  -5.000  -0.2418   0.05498   0.05076  -0.0716   0.9496   0.1567
  -4.750  -0.1768   0.03932   0.03330  -0.0897   0.9434   0.0750
  -4.500  -0.1431   0.03379   0.02705  -0.0920   0.9346   0.0615
  -4.250  -0.0997   0.02985   0.02256  -0.0959   0.9299   0.0600
  -4.000  -0.0637   0.02780   0.01985  -0.0974   0.9214   0.0622
  -3.750  -0.0203   0.02476   0.01639  -0.1002   0.9168   0.0636
  -3.500   0.0162   0.02286   0.01439  -0.1017   0.9099   0.0684
  -3.250   0.0537   0.02139   0.01281  -0.1033   0.9032   0.0812
  -3.000   0.0897   0.01989   0.01142  -0.1046   0.8967   0.1123
  -2.750   0.1216   0.01847   0.01043  -0.1055   0.8888   0.1973
  -2.500   0.1502   0.01675   0.00999  -0.1060   0.8819   0.4572
  -2.250   0.1736   0.01625   0.01002  -0.1042   0.8737   0.6418
  -2.000   0.1933   0.01607   0.01006  -0.1013   0.8654   0.7523
  -1.750   0.2129   0.01582   0.00993  -0.0978   0.8582   0.8498
  -1.500   0.2702   0.01538   0.00935  -0.1021   0.8532   0.9852
  -1.250   0.3022   0.01546   0.00912  -0.1037   0.8445   1.0000
  -1.000   0.3292   0.01566   0.00908  -0.1040   0.8359   1.0000
  -0.750   0.3597   0.01575   0.00893  -0.1046   0.8287   1.0000
  -0.500   0.3849   0.01605   0.00905  -0.1045   0.8198   1.0000
  -0.250   0.4155   0.01615   0.00896  -0.1049   0.8134   1.0000
   0.000   0.4398   0.01652   0.00920  -0.1046   0.8045   1.0000
   0.250   0.4702   0.01663   0.00915  -0.1049   0.7985   1.0000
   0.500   0.4938   0.01706   0.00949  -0.1045   0.7896   1.0000
   0.750   0.5238   0.01718   0.00950  -0.1047   0.7838   1.0000
   1.000   0.5471   0.01766   0.00992  -0.1043   0.7749   1.0000
   1.250   0.5767   0.01781   0.00997  -0.1044   0.7692   1.0000
   1.500   0.5997   0.01833   0.01047  -0.1040   0.7604   1.0000
   1.750   0.6291   0.01849   0.01057  -0.1040   0.7548   1.0000
   2.000   0.6518   0.01905   0.01113  -0.1036   0.7461   1.0000
   2.250   0.6811   0.01922   0.01125  -0.1035   0.7403   1.0000
   2.500   0.7035   0.01982   0.01187  -0.1031   0.7317   1.0000
   2.750   0.7327   0.01998   0.01203  -0.1030   0.7258   1.0000
   3.000   0.7549   0.02060   0.01269  -0.1025   0.7170   1.0000
   3.250   0.7845   0.02072   0.01280  -0.1024   0.7111   1.0000
   3.500   0.8062   0.02135   0.01350  -0.1018   0.7017   1.0000
   3.750   0.8368   0.02137   0.01354  -0.1016   0.6959   1.0000
   4.000   0.8581   0.02198   0.01425  -0.1009   0.6857   1.0000
   4.250   0.8862   0.02212   0.01441  -0.1005   0.6783   1.0000
   4.500   0.9116   0.02238   0.01474  -0.0999   0.6689   1.0000
   4.750   0.9353   0.02275   0.01524  -0.0991   0.6589   1.0000
   5.000   0.9675   0.02248   0.01498  -0.0988   0.6516   1.0000
   5.250   0.9900   0.02280   0.01543  -0.0979   0.6398   1.0000
   5.500   1.0148   0.02295   0.01568  -0.0970   0.6284   1.0000
   5.750   1.0418   0.02285   0.01570  -0.0961   0.6172   1.0000
   6.000   1.0709   0.02255   0.01546  -0.0954   0.6058   1.0000
   6.250   1.0997   0.02221   0.01518  -0.0946   0.5933   1.0000
   6.500   1.1258   0.02198   0.01508  -0.0935   0.5788   1.0000
   6.750   1.1492   0.02182   0.01509  -0.0921   0.5620   1.0000
   7.000   1.1727   0.02156   0.01497  -0.0907   0.5433   1.0000
   7.250   1.1981   0.02109   0.01459  -0.0893   0.5232   1.0000
   7.500   1.2192   0.02081   0.01448  -0.0874   0.4980   1.0000
   7.750   1.2387   0.02042   0.01413  -0.0851   0.4642   1.0000
   8.000   1.2510   0.02045   0.01412  -0.0820   0.4111   1.0000
   8.250   1.2579   0.02116   0.01448  -0.0785   0.3383   1.0000
   8.500   1.2588   0.02268   0.01550  -0.0748   0.2658   1.0000
   8.750   1.2557   0.02466   0.01705  -0.0709   0.2034   1.0000
   9.000   1.2464   0.02694   0.01891  -0.0664   0.1520   1.0000
   9.250   1.2329   0.02958   0.02114  -0.0617   0.1141   1.0000
   9.500   1.2220   0.03238   0.02369  -0.0578   0.0887   1.0000
   9.750   1.2188   0.03489   0.02611  -0.0550   0.0738   1.0000
  10.000   1.2208   0.03720   0.02837  -0.0528   0.0650   1.0000
  10.250   1.2321   0.03930   0.03052  -0.0509   0.0590   1.0000
  10.500   1.2491   0.04133   0.03248  -0.0495   0.0544   1.0000
  10.750   1.2811   0.04377   0.03500  -0.0490   0.0504   1.0000
  11.000   1.2997   0.04592   0.03737  -0.0480   0.0470   1.0000
  11.250   1.3236   0.04855   0.04016  -0.0475   0.0447   1.0000
  11.500   1.3527   0.05218   0.04400  -0.0477   0.0433   1.0000
  11.750   1.3729   0.05665   0.04880  -0.0475   0.0426   1.0000
  12.000   1.3775   0.06068   0.05319  -0.0459   0.0425   1.0000
  12.250   1.3743   0.06462   0.05746  -0.0439   0.0424   1.0000
  12.500   1.3660   0.06864   0.06180  -0.0420   0.0423   1.0000
  12.750   1.3536   0.07294   0.06640  -0.0404   0.0422   1.0000
  13.000   1.3383   0.07713   0.07087  -0.0392   0.0422   1.0000
  13.250   1.3212   0.08142   0.07543  -0.0386   0.0422   1.0000
  13.500   1.3024   0.08588   0.08015  -0.0387   0.0423   1.0000
  13.750   1.2819   0.09054   0.08508  -0.0395   0.0426   1.0000
  14.500   0.9778   0.11513   0.11116  -0.0487   0.0491   1.0000
  14.750   0.9418   0.12488   0.12105  -0.0553   0.0503   1.0000
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