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

E195 (11.82%) (e195-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 200,000
Max Cl/Cd: 78.22 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e195-il-200000-n5.txt
Download as CSV file: xf-e195-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E195  (11.82%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4035   0.08812   0.08458  -0.0431   1.0000   0.0179
  -9.750  -0.4107   0.08288   0.07940  -0.0454   1.0000   0.0175
  -9.500  -0.4208   0.07719   0.07377  -0.0481   1.0000   0.0176
  -9.250  -0.4375   0.07031   0.06698  -0.0517   1.0000   0.0175
  -9.000  -0.5087   0.05338   0.05004  -0.0628   1.0000   0.0161
  -8.500  -0.5165   0.04014   0.03600  -0.0727   0.9716   0.0165
  -8.250  -0.5023   0.03576   0.03115  -0.0751   0.9547   0.0168
  -8.000  -0.4845   0.03191   0.02677  -0.0766   0.9378   0.0170
  -7.750  -0.4629   0.02859   0.02292  -0.0777   0.9218   0.0171
  -7.500  -0.4385   0.02600   0.01987  -0.0783   0.9061   0.0172
  -7.250  -0.4132   0.02398   0.01746  -0.0786   0.8903   0.0175
  -7.000  -0.3881   0.02234   0.01549  -0.0786   0.8744   0.0177
  -6.750  -0.3633   0.02097   0.01384  -0.0783   0.8589   0.0181
  -6.500  -0.3391   0.01982   0.01243  -0.0778   0.8440   0.0185
  -6.250  -0.3150   0.01883   0.01124  -0.0771   0.8301   0.0189
  -6.000  -0.2910   0.01799   0.01020  -0.0765   0.8169   0.0194
  -5.750  -0.2672   0.01721   0.00927  -0.0758   0.8046   0.0201
  -5.500  -0.2437   0.01647   0.00844  -0.0752   0.7934   0.0215
  -5.250  -0.2193   0.01593   0.00777  -0.0747   0.7827   0.0228
  -5.000  -0.1946   0.01539   0.00710  -0.0741   0.7725   0.0239
  -4.750  -0.1696   0.01491   0.00647  -0.0736   0.7633   0.0251
  -4.500  -0.1443   0.01446   0.00589  -0.0731   0.7542   0.0269
  -4.250  -0.1188   0.01404   0.00538  -0.0727   0.7459   0.0306
  -4.000  -0.0932   0.01363   0.00492  -0.0723   0.7380   0.0401
  -3.750  -0.0680   0.01316   0.00455  -0.0719   0.7302   0.0697
  -3.500  -0.0427   0.01276   0.00425  -0.0716   0.7232   0.1111
  -3.250  -0.0172   0.01238   0.00402  -0.0714   0.7161   0.1580
  -3.000   0.0083   0.01204   0.00381  -0.0711   0.7094   0.2112
  -2.750   0.0333   0.01163   0.00366  -0.0708   0.7031   0.2866
  -2.500   0.0583   0.01130   0.00355  -0.0705   0.6967   0.3619
  -2.250   0.0838   0.01108   0.00346  -0.0701   0.6911   0.4255
  -2.000   0.1095   0.01089   0.00341  -0.0696   0.6848   0.4810
  -1.750   0.1354   0.01077   0.00334  -0.0692   0.6794   0.5252
  -1.500   0.1614   0.01065   0.00329  -0.0688   0.6737   0.5657
  -1.250   0.1872   0.01053   0.00326  -0.0683   0.6680   0.6066
  -1.000   0.2128   0.01043   0.00323  -0.0676   0.6633   0.6493
  -0.750   0.2382   0.01031   0.00323  -0.0670   0.6576   0.6945
  -0.500   0.2633   0.01020   0.00324  -0.0662   0.6523   0.7433
  -0.250   0.2889   0.01012   0.00325  -0.0653   0.6480   0.7967
   0.000   0.3179   0.01005   0.00331  -0.0651   0.6423   0.8545
   0.250   0.3565   0.01006   0.00333  -0.0670   0.6372   0.9076
   0.500   0.3985   0.01011   0.00331  -0.0699   0.6327   0.9471
   0.750   0.4386   0.01016   0.00333  -0.0725   0.6269   0.9744
   1.000   0.4801   0.01021   0.00332  -0.0755   0.6218   0.9920
   1.250   0.5139   0.01029   0.00333  -0.0769   0.6172   1.0000
   1.500   0.5380   0.01038   0.00340  -0.0763   0.6117   1.0000
   1.750   0.5625   0.01048   0.00346  -0.0757   0.6069   1.0000
   2.000   0.5871   0.01060   0.00353  -0.0751   0.6024   1.0000
   2.250   0.6117   0.01071   0.00365  -0.0745   0.5968   1.0000
   2.500   0.6365   0.01083   0.00374  -0.0740   0.5919   1.0000
   2.750   0.6615   0.01095   0.00385  -0.0735   0.5871   1.0000
   3.000   0.6864   0.01107   0.00401  -0.0729   0.5813   1.0000
   3.250   0.7117   0.01120   0.00411  -0.0724   0.5762   1.0000
   3.500   0.7367   0.01133   0.00427  -0.0719   0.5699   1.0000
   3.750   0.7618   0.01145   0.00441  -0.0714   0.5634   1.0000
   4.000   0.7868   0.01158   0.00457  -0.0709   0.5565   1.0000
   4.250   0.8118   0.01170   0.00471  -0.0703   0.5485   1.0000
   4.500   0.8366   0.01183   0.00487  -0.0698   0.5401   1.0000
   4.750   0.8615   0.01196   0.00500  -0.0692   0.5318   1.0000
   5.000   0.8860   0.01208   0.00521  -0.0686   0.5216   1.0000
   5.250   0.9105   0.01222   0.00539  -0.0680   0.5113   1.0000
   5.500   0.9348   0.01237   0.00556  -0.0673   0.5002   1.0000
   5.750   0.9586   0.01253   0.00575  -0.0666   0.4879   1.0000
   6.000   0.9822   0.01271   0.00598  -0.0658   0.4738   1.0000
   6.250   1.0053   0.01291   0.00623  -0.0649   0.4576   1.0000
   6.500   1.0278   0.01314   0.00649  -0.0640   0.4389   1.0000
   6.750   1.0488   0.01344   0.00676  -0.0628   0.4151   1.0000
   7.000   1.0673   0.01386   0.00710  -0.0613   0.3784   1.0000
   7.250   1.0813   0.01454   0.00754  -0.0591   0.3284   1.0000
   7.500   1.0905   0.01554   0.00821  -0.0563   0.2689   1.0000
   7.750   1.0975   0.01671   0.00904  -0.0534   0.2130   1.0000
   8.000   1.1069   0.01773   0.00986  -0.0509   0.1739   1.0000
   8.250   1.1161   0.01871   0.01069  -0.0483   0.1411   1.0000
   8.500   1.1230   0.01972   0.01156  -0.0455   0.1127   1.0000
   8.750   1.1281   0.02074   0.01246  -0.0424   0.0888   1.0000
   9.000   1.1319   0.02191   0.01348  -0.0393   0.0657   1.0000
   9.250   1.1379   0.02302   0.01453  -0.0368   0.0501   1.0000
   9.500   1.1433   0.02424   0.01571  -0.0344   0.0376   1.0000
   9.750   1.1482   0.02559   0.01704  -0.0321   0.0272   1.0000
  10.000   1.1523   0.02709   0.01855  -0.0301   0.0202   1.0000
  10.250   1.1577   0.02859   0.02009  -0.0283   0.0172   1.0000
  10.500   1.1633   0.03016   0.02177  -0.0267   0.0156   1.0000
  10.750   1.1691   0.03178   0.02349  -0.0253   0.0143   1.0000
  11.000   1.1743   0.03352   0.02532  -0.0241   0.0135   1.0000
  11.250   1.1778   0.03548   0.02737  -0.0230   0.0127   1.0000
  11.500   1.1821   0.03743   0.02942  -0.0220   0.0120   1.0000
  11.750   1.1863   0.03945   0.03157  -0.0212   0.0116   1.0000
  12.000   1.1903   0.04153   0.03376  -0.0205   0.0110   1.0000
  12.250   1.1931   0.04381   0.03616  -0.0198   0.0107   1.0000
  12.500   1.1942   0.04629   0.03875  -0.0193   0.0103   1.0000
  12.750   1.1960   0.04877   0.04135  -0.0189   0.0101   1.0000
  13.000   1.1968   0.05142   0.04413  -0.0186   0.0100   1.0000
  13.250   1.1965   0.05426   0.04707  -0.0184   0.0097   1.0000
  13.500   1.1947   0.05736   0.05027  -0.0183   0.0094   1.0000
  13.750   1.1956   0.06022   0.05325  -0.0183   0.0094   1.0000
  14.000   1.1938   0.06349   0.05661  -0.0184   0.0092   1.0000
  14.250   1.1915   0.06688   0.06010  -0.0186   0.0090   1.0000
  14.500   1.1926   0.06996   0.06330  -0.0188   0.0090   1.0000
  14.750   1.1935   0.07315   0.06664  -0.0192   0.0089   1.0000
  15.000   1.1939   0.07648   0.07011  -0.0197   0.0089   1.0000
  15.250   1.1931   0.08012   0.07391  -0.0203   0.0087   1.0000
  15.500   1.1919   0.08385   0.07780  -0.0211   0.0087   1.0000
  15.750   1.1901   0.08777   0.08188  -0.0222   0.0086   1.0000
  16.000   1.1871   0.09200   0.08629  -0.0234   0.0086   1.0000
  16.250   1.1827   0.09658   0.09107  -0.0250   0.0085   1.0000
  16.500   1.1767   0.10154   0.09622  -0.0269   0.0085   1.0000
  16.750   1.1696   0.10687   0.10174  -0.0291   0.0085   1.0000
  17.000   1.1609   0.11268   0.10774  -0.0319   0.0084   1.0000
  17.250   1.1520   0.11869   0.11392  -0.0349   0.0084   1.0000
  17.500   1.1406   0.12546   0.12089  -0.0386   0.0084   1.0000
  17.750   1.1290   0.13246   0.12808  -0.0425   0.0084   1.0000
  18.000   1.1160   0.14013   0.13593  -0.0471   0.0084   1.0000
  18.250   1.1021   0.14837   0.14435  -0.0522   0.0084   1.0000
  18.500   1.0877   0.15710   0.15324  -0.0577   0.0085   1.0000
  18.750   1.0690   0.16762   0.16392  -0.0643   0.0086   1.0000
  19.000   1.0502   0.17876   0.17518  -0.0712   0.0087   1.0000
<< Back to E195 (11.82%) (e195-il)

Polar data table (+)

Polar graphs


<< Back to E195 (11.82%) (e195-il)