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

E474 (14.09%) (e474-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E474 (14.09%) (e474-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.38 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e474-il-1000000.txt
Download as CSV file: xf-e474-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E474  (14.09%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -1.2163   0.08700   0.08331  -0.0258   1.0000   0.0225
 -18.250  -1.2576   0.07770   0.07386  -0.0305   1.0000   0.0222
 -18.000  -1.3005   0.06844   0.06443  -0.0350   1.0000   0.0219
 -17.750  -1.3412   0.05945   0.05527  -0.0394   1.0000   0.0217
 -17.500  -1.3740   0.05144   0.04708  -0.0436   1.0000   0.0217
 -17.250  -1.3970   0.04486   0.04034  -0.0471   1.0000   0.0220
 -17.000  -1.4118   0.03971   0.03504  -0.0497   1.0000   0.0225
 -16.750  -1.4206   0.03575   0.03097  -0.0513   1.0000   0.0230
 -16.500  -1.4310   0.03215   0.02726  -0.0520   1.0000   0.0240
 -16.250  -1.4359   0.02954   0.02457  -0.0517   1.0000   0.0251
 -16.000  -1.4373   0.02755   0.02250  -0.0507   1.0000   0.0266
 -15.750  -1.4376   0.02585   0.02073  -0.0492   1.0000   0.0280
 -15.500  -1.4378   0.02432   0.01916  -0.0471   1.0000   0.0300
 -15.250  -1.4328   0.02322   0.01800  -0.0451   1.0000   0.0319
 -15.000  -1.4301   0.02206   0.01682  -0.0426   1.0000   0.0344
 -14.750  -1.4238   0.02116   0.01589  -0.0402   1.0000   0.0371
 -14.500  -1.4173   0.02031   0.01501  -0.0376   1.0000   0.0396
 -14.250  -1.4100   0.01955   0.01423  -0.0349   1.0000   0.0427
 -14.000  -1.4010   0.01893   0.01358  -0.0321   1.0000   0.0454
 -13.750  -1.3943   0.01828   0.01292  -0.0289   1.0000   0.0487
 -13.500  -1.3834   0.01781   0.01243  -0.0262   1.0000   0.0512
 -13.250  -1.3722   0.01719   0.01182  -0.0236   1.0000   0.0550
 -13.000  -1.3579   0.01671   0.01132  -0.0214   1.0000   0.0584
 -12.750  -1.3437   0.01622   0.01082  -0.0192   1.0000   0.0621
 -12.500  -1.3293   0.01573   0.01034  -0.0169   1.0000   0.0665
 -12.250  -1.3135   0.01533   0.00993  -0.0148   1.0000   0.0702
 -12.000  -1.2990   0.01488   0.00949  -0.0125   1.0000   0.0748
 -11.500  -1.2679   0.01411   0.00874  -0.0081   1.0000   0.0841
 -11.250  -1.2512   0.01380   0.00841  -0.0060   1.0000   0.0880
 -11.000  -1.2346   0.01346   0.00807  -0.0039   1.0000   0.0925
 -10.750  -1.2178   0.01313   0.00776  -0.0019   1.0000   0.0973
 -10.500  -1.1990   0.01290   0.00750  -0.0001   1.0000   0.1005
 -10.250  -1.1815   0.01257   0.00718   0.0018   1.0000   0.1053
 -10.000  -1.1626   0.01230   0.00691   0.0036   1.0000   0.1096
  -9.750  -1.1424   0.01210   0.00669   0.0051   1.0000   0.1127
  -9.500  -1.1234   0.01180   0.00641   0.0068   1.0000   0.1180
  -9.250  -1.1031   0.01157   0.00619   0.0083   1.0000   0.1226
  -9.000  -1.0817   0.01141   0.00601   0.0096   1.0000   0.1262
  -8.750  -1.0617   0.01114   0.00577   0.0112   1.0000   0.1321
  -8.500  -1.0383   0.01096   0.00560   0.0121   0.9998   0.1365
  -8.250  -1.0040   0.01083   0.00544   0.0108   0.9985   0.1397
  -8.000  -0.9692   0.01058   0.00523   0.0093   0.9967   0.1457
  -7.750  -0.9311   0.01043   0.00509   0.0073   0.9948   0.1503
  -7.500  -0.8891   0.01032   0.00495   0.0044   0.9931   0.1540
  -7.250  -0.8520   0.01005   0.00474   0.0026   0.9899   0.1598
  -7.000  -0.8104   0.00987   0.00457  -0.0002   0.9866   0.1646
  -6.750  -0.7657   0.00971   0.00439  -0.0035   0.9840   0.1684
  -6.500  -0.7214   0.00944   0.00417  -0.0068   0.9821   0.1744
  -6.250  -0.6847   0.00927   0.00402  -0.0085   0.9799   0.1787
  -6.000  -0.6536   0.00916   0.00389  -0.0090   0.9765   0.1816
  -5.750  -0.6185   0.00893   0.00369  -0.0103   0.9739   0.1863
  -5.500  -0.5825   0.00874   0.00353  -0.0119   0.9712   0.1910
  -5.250  -0.5474   0.00859   0.00339  -0.0131   0.9687   0.1948
  -5.000  -0.5199   0.00850   0.00327  -0.0128   0.9630   0.1970
  -4.750  -0.4911   0.00828   0.00309  -0.0127   0.9566   0.2021
  -4.500  -0.4629   0.00813   0.00296  -0.0125   0.9493   0.2063
  -4.250  -0.4356   0.00801   0.00283  -0.0120   0.9401   0.2098
  -4.000  -0.4087   0.00792   0.00272  -0.0114   0.9294   0.2123
  -3.750  -0.3823   0.00777   0.00257  -0.0108   0.9153   0.2168
  -3.500  -0.3562   0.00764   0.00243  -0.0100   0.8910   0.2214
  -3.250  -0.3314   0.00763   0.00227  -0.0089   0.8375   0.2252
  -3.000  -0.3088   0.00781   0.00215  -0.0074   0.7599   0.2280
  -2.750  -0.2858   0.00795   0.00207  -0.0062   0.6926   0.2323
  -2.500  -0.2618   0.00807   0.00201  -0.0052   0.6322   0.2375
  -2.250  -0.2370   0.00821   0.00196  -0.0044   0.5757   0.2421
  -2.000  -0.2114   0.00834   0.00192  -0.0037   0.5249   0.2456
  -1.750  -0.1860   0.00840   0.00187  -0.0031   0.4824   0.2520
  -1.250  -0.1333   0.00853   0.00180  -0.0021   0.4161   0.2641
  -1.000  -0.1069   0.00856   0.00178  -0.0017   0.3891   0.2719
  -0.750  -0.0802   0.00862   0.00176  -0.0012   0.3643   0.2789
  -0.500  -0.0537   0.00863   0.00174  -0.0008   0.3437   0.2893
  -0.250  -0.0269   0.00865   0.00173  -0.0004   0.3270   0.3002
   0.000   0.0000   0.00866   0.00173   0.0000   0.3124   0.3124
   0.250   0.0269   0.00865   0.00173   0.0004   0.3002   0.3270
   0.500   0.0537   0.00863   0.00174   0.0008   0.2891   0.3438
   0.750   0.0802   0.00862   0.00176   0.0012   0.2789   0.3641
   1.000   0.1069   0.00856   0.00178   0.0017   0.2719   0.3893
   1.250   0.1333   0.00853   0.00180   0.0021   0.2642   0.4161
   1.500   0.1598   0.00847   0.00183   0.0026   0.2580   0.4469
   1.750   0.1860   0.00840   0.00187   0.0031   0.2520   0.4824
   2.000   0.2114   0.00834   0.00192   0.0037   0.2458   0.5244
   2.250   0.2370   0.00821   0.00196   0.0044   0.2421   0.5755
   2.500   0.2618   0.00807   0.00201   0.0052   0.2375   0.6322
   2.750   0.2858   0.00795   0.00207   0.0062   0.2324   0.6926
   3.000   0.3088   0.00781   0.00215   0.0074   0.2280   0.7597
   3.250   0.3314   0.00763   0.00226   0.0089   0.2252   0.8370
   3.500   0.3562   0.00764   0.00243   0.0100   0.2214   0.8913
   3.750   0.3823   0.00776   0.00257   0.0108   0.2168   0.9153
   4.000   0.4087   0.00792   0.00272   0.0114   0.2123   0.9294
   4.250   0.4356   0.00801   0.00283   0.0120   0.2097   0.9402
   4.500   0.4630   0.00813   0.00296   0.0124   0.2063   0.9491
   4.750   0.4910   0.00828   0.00309   0.0127   0.2021   0.9565
   5.000   0.5199   0.00849   0.00327   0.0128   0.1970   0.9629
   5.250   0.5474   0.00859   0.00339   0.0131   0.1948   0.9687
   5.500   0.5829   0.00874   0.00354   0.0118   0.1912   0.9713
   5.750   0.6188   0.00893   0.00369   0.0103   0.1863   0.9740
   6.000   0.6536   0.00916   0.00389   0.0090   0.1816   0.9766
   6.250   0.6847   0.00927   0.00402   0.0085   0.1786   0.9799
   6.500   0.7217   0.00944   0.00417   0.0068   0.1745   0.9821
   6.750   0.7656   0.00970   0.00439   0.0035   0.1684   0.9840
   7.000   0.8102   0.00987   0.00457   0.0002   0.1648   0.9866
   7.250   0.8519   0.01005   0.00474  -0.0026   0.1598   0.9899
   7.500   0.8891   0.01032   0.00495  -0.0044   0.1538   0.9931
   7.750   0.9312   0.01043   0.00509  -0.0073   0.1503   0.9948
   8.000   0.9694   0.01058   0.00523  -0.0094   0.1458   0.9967
   8.250   1.0042   0.01083   0.00543  -0.0108   0.1397   0.9985
   8.500   1.0384   0.01096   0.00560  -0.0121   0.1365   0.9998
   8.750   1.0616   0.01113   0.00577  -0.0111   0.1322   1.0000
   9.000   1.0817   0.01141   0.00600  -0.0096   0.1265   1.0000
   9.250   1.1031   0.01157   0.00619  -0.0083   0.1228   1.0000
   9.500   1.1233   0.01180   0.00641  -0.0068   0.1179   1.0000
   9.750   1.1424   0.01210   0.00669  -0.0051   0.1126   1.0000
  10.000   1.1625   0.01229   0.00691  -0.0036   0.1096   1.0000
  10.250   1.1814   0.01256   0.00718  -0.0018   0.1054   1.0000
  10.500   1.1989   0.01290   0.00750   0.0001   0.1005   1.0000
  10.750   1.2177   0.01313   0.00776   0.0019   0.0971   1.0000
  11.000   1.2346   0.01346   0.00807   0.0039   0.0925   1.0000
  11.250   1.2511   0.01380   0.00841   0.0060   0.0882   1.0000
  11.500   1.2677   0.01412   0.00874   0.0081   0.0838   1.0000
  11.750   1.2823   0.01456   0.00915   0.0105   0.0785   1.0000
  12.000   1.2990   0.01487   0.00949   0.0125   0.0749   1.0000
  12.250   1.3134   0.01534   0.00993   0.0148   0.0700   1.0000
  12.500   1.3293   0.01574   0.01034   0.0169   0.0663   1.0000
  12.750   1.3437   0.01623   0.01082   0.0192   0.0620   1.0000
  13.000   1.3581   0.01671   0.01132   0.0214   0.0584   1.0000
  13.250   1.3723   0.01720   0.01182   0.0236   0.0550   1.0000
  13.500   1.3837   0.01781   0.01242   0.0261   0.0512   1.0000
  13.750   1.3946   0.01828   0.01293   0.0289   0.0486   1.0000
  14.000   1.4014   0.01893   0.01358   0.0321   0.0454   1.0000
  14.250   1.4103   0.01956   0.01423   0.0348   0.0424   1.0000
  14.500   1.4184   0.02028   0.01499   0.0374   0.0399   1.0000
  14.750   1.4243   0.02116   0.01588   0.0401   0.0370   1.0000
  15.000   1.4312   0.02203   0.01679   0.0425   0.0346   1.0000
  15.250   1.4337   0.02320   0.01799   0.0450   0.0321   1.0000
  15.500   1.4384   0.02432   0.01916   0.0470   0.0299   1.0000
  15.750   1.4385   0.02583   0.02072   0.0490   0.0280   1.0000
  16.000   1.4386   0.02751   0.02246   0.0505   0.0264   1.0000
  16.250   1.4380   0.02944   0.02447   0.0515   0.0252   1.0000
  16.500   1.4317   0.03218   0.02728   0.0518   0.0239   1.0000
  16.750   1.4223   0.03569   0.03089   0.0511   0.0229   1.0000
  17.000   1.4138   0.03962   0.03495   0.0496   0.0223   1.0000
  17.250   1.3999   0.04466   0.04013   0.0470   0.0219   1.0000
  17.500   1.3779   0.05112   0.04675   0.0435   0.0218   1.0000
  17.750   1.3445   0.05925   0.05506   0.0392   0.0217   1.0000
  18.000   1.3043   0.06819   0.06418   0.0348   0.0219   1.0000
  18.250   1.2609   0.07753   0.07368   0.0302   0.0221   1.0000
  18.500   1.2205   0.08669   0.08299   0.0257   0.0223   1.0000
<< Back to E474 (14.09%) (e474-il)

Polar data table (+)

Polar graphs


<< Back to E474 (14.09%) (e474-il)