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E197 (13.49%) (e197-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E197 (13.49%) (e197-il)
Reynolds number: 100,000
Max Cl/Cd: 52.51 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e197-il-100000.txt
Download as CSV file: xf-e197-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E197  (13.49%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3740   0.10928   0.10437  -0.0367   1.0000   0.1284
 -10.250  -0.3693   0.10613   0.10126  -0.0373   1.0000   0.1328
 -10.000  -0.4208   0.10296   0.09831  -0.0460   1.0000   0.1384
  -9.750  -0.3809   0.09861   0.09390  -0.0409   1.0000   0.1411
  -9.500  -0.3687   0.09600   0.09130  -0.0399   1.0000   0.1468
  -9.250  -0.4160   0.09217   0.08770  -0.0469   1.0000   0.1526
  -9.000  -0.3812   0.08889   0.08436  -0.0423   1.0000   0.1566
  -8.750  -0.3779   0.08605   0.08158  -0.0418   1.0000   0.1616
  -8.500  -0.4359   0.08270   0.07853  -0.0463   1.0000   0.1669
  -8.000  -0.6070   0.06088   0.05641  -0.0480   0.9973   0.0812
  -7.750  -0.5996   0.05015   0.04484  -0.0539   0.9859   0.0678
  -7.500  -0.5769   0.04454   0.03880  -0.0572   0.9764   0.0655
  -7.250  -0.5507   0.04001   0.03366  -0.0600   0.9673   0.0653
  -7.000  -0.5205   0.03634   0.02937  -0.0623   0.9586   0.0662
  -6.750  -0.4914   0.03328   0.02576  -0.0636   0.9493   0.0666
  -6.500  -0.4530   0.03051   0.02243  -0.0660   0.9433   0.0678
  -6.250  -0.4213   0.02842   0.01995  -0.0669   0.9344   0.0700
  -6.000  -0.3802   0.02644   0.01801  -0.0699   0.9292   0.0766
  -5.750  -0.3458   0.02496   0.01631  -0.0710   0.9214   0.0831
  -5.500  -0.3091   0.02335   0.01475  -0.0727   0.9152   0.0949
  -5.250  -0.2814   0.02194   0.01355  -0.0731   0.9072   0.1212
  -5.000  -0.2543   0.02029   0.01234  -0.0735   0.8998   0.1868
  -4.750  -0.2328   0.01932   0.01180  -0.0730   0.8908   0.2699
  -4.500  -0.2059   0.01864   0.01161  -0.0731   0.8841   0.3770
  -4.250  -0.1848   0.01861   0.01173  -0.0716   0.8750   0.4468
  -4.000  -0.1551   0.01855   0.01169  -0.0715   0.8688   0.5024
  -3.750  -0.1338   0.01869   0.01178  -0.0700   0.8602   0.5434
  -3.500  -0.1053   0.01866   0.01178  -0.0694   0.8541   0.5805
  -3.250  -0.0834   0.01878   0.01189  -0.0679   0.8463   0.6116
  -3.000  -0.0570   0.01878   0.01186  -0.0671   0.8399   0.6413
  -2.750  -0.0331   0.01884   0.01188  -0.0660   0.8332   0.6686
  -2.500  -0.0098   0.01889   0.01192  -0.0647   0.8261   0.6944
  -2.250   0.0198   0.01879   0.01179  -0.0641   0.8217   0.7201
  -2.000   0.0363   0.01903   0.01203  -0.0621   0.8129   0.7441
  -1.750   0.0641   0.01896   0.01194  -0.0613   0.8080   0.7692
  -1.500   0.0828   0.01918   0.01219  -0.0595   0.8004   0.7935
  -1.250   0.1084   0.01920   0.01219  -0.0585   0.7948   0.8205
  -1.000   0.1359   0.01926   0.01223  -0.0577   0.7897   0.8484
  -0.750   0.1619   0.01955   0.01254  -0.0572   0.7824   0.8768
  -0.500   0.2069   0.01957   0.01248  -0.0596   0.7783   0.9037
  -0.250   0.2548   0.01982   0.01267  -0.0634   0.7725   0.9294
   0.000   0.3141   0.01995   0.01270  -0.0697   0.7669   0.9504
   0.250   0.3785   0.01982   0.01244  -0.0767   0.7628   0.9693
   0.500   0.4422   0.01986   0.01243  -0.0847   0.7567   0.9881
   0.750   0.4852   0.01984   0.01234  -0.0890   0.7504   1.0000
   1.000   0.4942   0.02001   0.01243  -0.0867   0.7451   1.0000
   1.250   0.4960   0.02069   0.01310  -0.0836   0.7365   1.0000
   1.500   0.5167   0.02082   0.01314  -0.0824   0.7319   1.0000
   1.750   0.5226   0.02171   0.01402  -0.0797   0.7234   1.0000
   2.000   0.5454   0.02193   0.01417  -0.0788   0.7183   1.0000
   2.250   0.5581   0.02269   0.01492  -0.0769   0.7111   1.0000
   2.500   0.5772   0.02316   0.01537  -0.0756   0.7047   1.0000
   2.750   0.6076   0.02316   0.01532  -0.0755   0.7011   1.0000
   3.000   0.6119   0.02442   0.01663  -0.0729   0.6913   1.0000
   3.250   0.6422   0.02442   0.01662  -0.0728   0.6871   1.0000
   3.500   0.6498   0.02564   0.01789  -0.0705   0.6778   1.0000
   3.750   0.6792   0.02568   0.01793  -0.0703   0.6729   1.0000
   4.000   0.6908   0.02672   0.01902  -0.0684   0.6642   1.0000
   4.250   0.7189   0.02680   0.01914  -0.0681   0.6585   1.0000
   4.500   0.7344   0.02764   0.02003  -0.0666   0.6501   1.0000
   4.750   0.7624   0.02767   0.02010  -0.0661   0.6437   1.0000
   5.000   0.7795   0.02838   0.02088  -0.0647   0.6351   1.0000
   5.250   0.8101   0.02819   0.02076  -0.0644   0.6285   1.0000
   5.500   0.8264   0.02887   0.02152  -0.0629   0.6189   1.0000
   5.750   0.8638   0.02817   0.02087  -0.0631   0.6129   1.0000
   6.000   0.8789   0.02882   0.02164  -0.0613   0.6023   1.0000
   6.250   0.9242   0.02750   0.02036  -0.0621   0.5967   1.0000
   6.500   0.9406   0.02788   0.02088  -0.0602   0.5849   1.0000
   6.750   0.9662   0.02765   0.02074  -0.0591   0.5745   1.0000
   7.000   1.0114   0.02610   0.01923  -0.0598   0.5664   1.0000
   7.250   1.0336   0.02585   0.01911  -0.0583   0.5533   1.0000
   7.500   1.0591   0.02532   0.01870  -0.0570   0.5399   1.0000
   7.750   1.0864   0.02460   0.01809  -0.0558   0.5254   1.0000
   8.000   1.1141   0.02379   0.01736  -0.0546   0.5095   1.0000
   8.250   1.1387   0.02310   0.01674  -0.0531   0.4912   1.0000
   8.500   1.1547   0.02281   0.01660  -0.0505   0.4689   1.0000
   8.750   1.1708   0.02252   0.01639  -0.0479   0.4430   1.0000
   9.000   1.1819   0.02251   0.01640  -0.0447   0.4109   1.0000
   9.250   1.1873   0.02285   0.01665  -0.0409   0.3720   1.0000
   9.500   1.1843   0.02366   0.01726  -0.0362   0.3277   1.0000
   9.750   1.1740   0.02496   0.01825  -0.0309   0.2864   1.0000
  10.000   1.1624   0.02674   0.01972  -0.0263   0.2492   1.0000
  10.250   1.1509   0.02888   0.02155  -0.0224   0.2175   1.0000
  10.500   1.1410   0.03122   0.02364  -0.0194   0.1891   1.0000
  10.750   1.1334   0.03364   0.02591  -0.0170   0.1635   1.0000
  11.000   1.1278   0.03612   0.02823  -0.0150   0.1415   1.0000
  11.250   1.1227   0.03868   0.03065  -0.0134   0.1226   1.0000
  11.500   1.1192   0.04129   0.03310  -0.0119   0.1058   1.0000
  11.750   1.1177   0.04386   0.03564  -0.0106   0.0905   1.0000
  12.000   1.1166   0.04653   0.03825  -0.0093   0.0767   1.0000
  12.250   1.1220   0.04887   0.04050  -0.0079   0.0662   1.0000
  12.500   1.1328   0.05090   0.04240  -0.0066   0.0583   1.0000
  12.750   1.1433   0.05313   0.04481  -0.0055   0.0523   1.0000
  13.000   1.1679   0.05507   0.04655  -0.0043   0.0467   1.0000
  13.250   1.1794   0.05753   0.04933  -0.0033   0.0449   1.0000
  13.500   1.1905   0.06036   0.05245  -0.0024   0.0431   1.0000
  13.750   1.1981   0.06347   0.05584  -0.0017   0.0420   1.0000
  14.000   1.2005   0.06691   0.05953  -0.0011   0.0411   1.0000
  14.250   1.1989   0.07040   0.06324  -0.0008   0.0402   1.0000
  14.500   1.1935   0.07432   0.06740  -0.0008   0.0398   1.0000
  14.750   1.1843   0.07863   0.07195  -0.0011   0.0395   1.0000
  15.000   1.1759   0.08285   0.07633  -0.0017   0.0387   1.0000
  15.250   1.1613   0.08785   0.08156  -0.0028   0.0386   1.0000
  15.500   1.1261   0.09555   0.08972  -0.0056   0.0400   1.0000
  15.750   1.0915   0.10395   0.09845  -0.0097   0.0407   1.0000
  16.000   1.0520   0.11437   0.10919  -0.0155   0.0421   1.0000
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