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E197 (13.49%) (e197-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E197 (13.49%) (e197-il)
Reynolds number: 200,000
Max Cl/Cd: 77.59 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e197-il-200000.txt
Download as CSV file: xf-e197-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3896   0.10330   0.09979  -0.0410   1.0000   0.0660
 -10.500  -0.4297   0.09402   0.09065  -0.0530   1.0000   0.0693
 -10.250  -0.4338   0.08817   0.08487  -0.0536   1.0000   0.0703
 -10.000  -0.4179   0.08703   0.08372  -0.0503   1.0000   0.0714
  -9.750  -0.4017   0.08647   0.08315  -0.0478   1.0000   0.0742
  -9.500  -0.4050   0.08262   0.07935  -0.0493   1.0000   0.0760
  -9.250  -0.4173   0.07743   0.07424  -0.0523   1.0000   0.0780
  -9.000  -0.4406   0.07065   0.06757  -0.0571   1.0000   0.0784
  -8.750  -0.4813   0.06490   0.06192  -0.0599   1.0000   0.0772
  -8.500  -0.5118   0.06129   0.05832  -0.0597   0.9951   0.0765
  -8.250  -0.5597   0.03455   0.02890  -0.0706   0.9659   0.0366
  -8.000  -0.5294   0.03069   0.02458  -0.0731   0.9579   0.0367
  -7.750  -0.5000   0.02776   0.02126  -0.0744   0.9465   0.0367
  -7.500  -0.4699   0.02471   0.01790  -0.0757   0.9359   0.0372
  -7.250  -0.4375   0.02256   0.01558  -0.0770   0.9259   0.0382
  -7.000  -0.4083   0.02125   0.01417  -0.0775   0.9131   0.0400
  -6.750  -0.3814   0.02030   0.01308  -0.0773   0.8992   0.0424
  -6.500  -0.3562   0.01926   0.01189  -0.0767   0.8855   0.0442
  -6.250  -0.3319   0.01842   0.01089  -0.0758   0.8724   0.0458
  -6.000  -0.3116   0.01714   0.00959  -0.0746   0.8602   0.0488
  -5.750  -0.2891   0.01646   0.00883  -0.0736   0.8491   0.0533
  -5.500  -0.2676   0.01570   0.00801  -0.0725   0.8383   0.0612
  -5.250  -0.2467   0.01484   0.00718  -0.0713   0.8278   0.0836
  -5.000  -0.2264   0.01388   0.00651  -0.0702   0.8191   0.1437
  -4.750  -0.2038   0.01332   0.00613  -0.0696   0.8099   0.2008
  -4.500  -0.1810   0.01283   0.00585  -0.0689   0.8018   0.2636
  -4.250  -0.1584   0.01239   0.00567  -0.0682   0.7941   0.3398
  -4.000  -0.1349   0.01218   0.00565  -0.0674   0.7865   0.4119
  -3.750  -0.1100   0.01211   0.00560  -0.0667   0.7794   0.4611
  -3.500  -0.0844   0.01208   0.00556  -0.0662   0.7729   0.4938
  -3.250  -0.0586   0.01205   0.00551  -0.0657   0.7659   0.5216
  -3.000  -0.0324   0.01205   0.00545  -0.0652   0.7604   0.5483
  -2.750  -0.0067   0.01205   0.00544  -0.0647   0.7534   0.5734
  -2.500   0.0197   0.01201   0.00539  -0.0642   0.7480   0.5947
  -2.250   0.0458   0.01201   0.00537  -0.0638   0.7421   0.6155
  -2.000   0.0721   0.01199   0.00534  -0.0634   0.7361   0.6362
  -1.750   0.0989   0.01196   0.00530  -0.0630   0.7315   0.6560
  -1.500   0.1245   0.01195   0.00533  -0.0625   0.7253   0.6770
  -1.250   0.1508   0.01192   0.00532  -0.0620   0.7199   0.6986
  -1.000   0.1775   0.01191   0.00530  -0.0616   0.7156   0.7206
  -0.750   0.2026   0.01190   0.00538  -0.0610   0.7096   0.7446
  -0.500   0.2282   0.01186   0.00540  -0.0603   0.7045   0.7711
  -0.250   0.2542   0.01185   0.00542  -0.0596   0.7004   0.8002
   0.000   0.2784   0.01185   0.00556  -0.0586   0.6945   0.8331
   0.250   0.3054   0.01186   0.00563  -0.0580   0.6896   0.8681
   0.500   0.3389   0.01194   0.00568  -0.0586   0.6857   0.9018
   0.750   0.3777   0.01207   0.00586  -0.0608   0.6797   0.9314
   1.000   0.4205   0.01217   0.00592  -0.0637   0.6747   0.9561
   1.250   0.4694   0.01228   0.00592  -0.0680   0.6707   0.9717
   1.500   0.5191   0.01238   0.00604  -0.0729   0.6644   0.9855
   1.750   0.5702   0.01239   0.00601  -0.0780   0.6592   0.9976
   2.000   0.5972   0.01249   0.00604  -0.0783   0.6551   1.0000
   2.250   0.6155   0.01265   0.00624  -0.0769   0.6490   1.0000
   2.500   0.6374   0.01278   0.00632  -0.0760   0.6441   1.0000
   2.750   0.6609   0.01294   0.00643  -0.0752   0.6399   1.0000
   3.000   0.6816   0.01314   0.00670  -0.0741   0.6336   1.0000
   3.250   0.7056   0.01328   0.00680  -0.0734   0.6287   1.0000
   3.500   0.7295   0.01346   0.00697  -0.0728   0.6237   1.0000
   3.750   0.7518   0.01363   0.00721  -0.0718   0.6170   1.0000
   4.000   0.7775   0.01372   0.00725  -0.0713   0.6120   1.0000
   4.250   0.7995   0.01391   0.00750  -0.0703   0.6047   1.0000
   4.500   0.8246   0.01397   0.00755  -0.0697   0.5984   1.0000
   4.750   0.8482   0.01411   0.00774  -0.0689   0.5913   1.0000
   5.000   0.8729   0.01416   0.00781  -0.0682   0.5841   1.0000
   5.250   0.8970   0.01425   0.00795  -0.0674   0.5766   1.0000
   5.500   0.9219   0.01427   0.00799  -0.0667   0.5686   1.0000
   5.750   0.9453   0.01435   0.00814  -0.0659   0.5599   1.0000
   6.000   0.9716   0.01431   0.00808  -0.0654   0.5519   1.0000
   6.250   0.9936   0.01436   0.00825  -0.0642   0.5413   1.0000
   6.500   1.0172   0.01437   0.00833  -0.0633   0.5310   1.0000
   6.750   1.0415   0.01435   0.00833  -0.0625   0.5202   1.0000
   7.000   1.0643   0.01435   0.00838  -0.0614   0.5077   1.0000
   7.250   1.0859   0.01437   0.00847  -0.0601   0.4932   1.0000
   7.500   1.1067   0.01445   0.00863  -0.0588   0.4767   1.0000
   7.750   1.1263   0.01457   0.00883  -0.0573   0.4569   1.0000
   8.000   1.1452   0.01476   0.00902  -0.0556   0.4350   1.0000
   8.250   1.1618   0.01506   0.00932  -0.0536   0.4074   1.0000
   8.500   1.1748   0.01553   0.00972  -0.0512   0.3701   1.0000
   8.750   1.1804   0.01634   0.01028  -0.0476   0.3202   1.0000
   9.000   1.1795   0.01748   0.01111  -0.0434   0.2684   1.0000
   9.250   1.1739   0.01871   0.01208  -0.0385   0.2268   1.0000
   9.500   1.1679   0.02007   0.01321  -0.0339   0.1912   1.0000
   9.750   1.1641   0.02153   0.01450  -0.0302   0.1616   1.0000
  10.000   1.1629   0.02303   0.01588  -0.0272   0.1370   1.0000
  10.250   1.1618   0.02469   0.01745  -0.0245   0.1167   1.0000
  10.500   1.1609   0.02649   0.01917  -0.0223   0.0976   1.0000
  10.750   1.1590   0.02851   0.02109  -0.0203   0.0820   1.0000
  11.000   1.1573   0.03066   0.02321  -0.0186   0.0680   1.0000
  11.250   1.1548   0.03302   0.02553  -0.0170   0.0541   1.0000
  11.500   1.1486   0.03580   0.02828  -0.0154   0.0442   1.0000
  11.750   1.1425   0.03870   0.03115  -0.0141   0.0379   1.0000
  12.000   1.1415   0.04123   0.03377  -0.0130   0.0331   1.0000
  12.250   1.1410   0.04376   0.03633  -0.0122   0.0309   1.0000
  12.500   1.1366   0.04666   0.03922  -0.0110   0.0292   1.0000
  12.750   1.1421   0.04875   0.04145  -0.0103   0.0273   1.0000
  13.000   1.1466   0.05095   0.04371  -0.0099   0.0252   1.0000
  13.250   1.1508   0.05320   0.04600  -0.0093   0.0242   1.0000
  13.500   1.1543   0.05558   0.04835  -0.0082   0.0227   1.0000
  13.750   1.1634   0.05750   0.05041  -0.0074   0.0222   1.0000
  14.000   1.1718   0.05959   0.05265  -0.0068   0.0215   1.0000
  14.250   1.1800   0.06179   0.05499  -0.0061   0.0208   1.0000
  14.500   1.1884   0.06406   0.05740  -0.0056   0.0204   1.0000
  14.750   1.1949   0.06661   0.06011  -0.0051   0.0201   1.0000
  15.000   1.1989   0.06950   0.06317  -0.0049   0.0196   1.0000
  15.250   1.2009   0.07271   0.06656  -0.0049   0.0194   1.0000
  15.500   1.1996   0.07642   0.07050  -0.0052   0.0194   1.0000
  15.750   1.1953   0.08051   0.07479  -0.0058   0.0192   1.0000
  16.000   1.1873   0.08522   0.07974  -0.0068   0.0192   1.0000
  16.250   1.1764   0.09045   0.08520  -0.0084   0.0192   1.0000
  16.500   1.1598   0.09676   0.09180  -0.0107   0.0194   1.0000
  16.750   1.1414   0.10362   0.09893  -0.0137   0.0196   1.0000
  17.000   1.1209   0.11120   0.10675  -0.0175   0.0197   1.0000
  17.250   1.0971   0.11986   0.11566  -0.0222   0.0200   1.0000
  17.500   1.0722   0.12933   0.12536  -0.0279   0.0204   1.0000
  17.750   1.0455   0.13991   0.13615  -0.0345   0.0208   1.0000
  18.000   1.0162   0.15216   0.14858  -0.0424   0.0212   1.0000
  18.250   0.9835   0.16669   0.16322  -0.0516   0.0219   1.0000
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