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=500,000 Ncrit=9


Details Polar file
Airfoil: E474 (14.09%) (e474-il)
Reynolds number: 500,000
Max Cl/Cd: 73.51 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e474-il-500000.txt
Download as CSV file: xf-e474-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.1687   0.08383   0.07970  -0.0271   1.0000   0.0387
 -17.500  -1.1976   0.07631   0.07209  -0.0309   1.0000   0.0392
 -17.250  -1.2277   0.06882   0.06448  -0.0346   1.0000   0.0396
 -17.000  -1.2580   0.06132   0.05684  -0.0383   1.0000   0.0400
 -16.750  -1.2848   0.05426   0.04965  -0.0418   1.0000   0.0403
 -16.500  -1.3083   0.04767   0.04291  -0.0453   1.0000   0.0412
 -16.250  -1.3238   0.04240   0.03750  -0.0479   1.0000   0.0423
 -16.000  -1.3311   0.03854   0.03348  -0.0495   1.0000   0.0440
 -15.750  -1.3451   0.03441   0.02926  -0.0506   1.0000   0.0457
 -15.500  -1.3523   0.03149   0.02626  -0.0505   1.0000   0.0479
 -15.250  -1.3529   0.02948   0.02416  -0.0497   1.0000   0.0504
 -15.000  -1.3543   0.02762   0.02223  -0.0482   1.0000   0.0530
 -14.750  -1.3543   0.02605   0.02061  -0.0464   1.0000   0.0557
 -14.500  -1.3477   0.02498   0.01946  -0.0446   1.0000   0.0589
 -14.250  -1.3453   0.02375   0.01820  -0.0422   1.0000   0.0622
 -14.000  -1.3386   0.02282   0.01724  -0.0399   1.0000   0.0658
 -13.750  -1.3286   0.02210   0.01644  -0.0378   1.0000   0.0690
 -13.500  -1.3230   0.02122   0.01557  -0.0350   1.0000   0.0729
 -13.250  -1.3124   0.02062   0.01493  -0.0325   1.0000   0.0768
 -13.000  -1.3034   0.02001   0.01427  -0.0297   1.0000   0.0805
 -12.750  -1.2942   0.01943   0.01369  -0.0269   1.0000   0.0846
 -12.500  -1.2789   0.01900   0.01321  -0.0249   1.0000   0.0885
 -12.250  -1.2664   0.01843   0.01263  -0.0225   1.0000   0.0928
 -12.000  -1.2513   0.01798   0.01217  -0.0204   1.0000   0.0973
 -11.750  -1.2336   0.01766   0.01177  -0.0187   1.0000   0.1012
 -11.500  -1.2200   0.01713   0.01127  -0.0163   1.0000   0.1057
 -11.250  -1.2029   0.01679   0.01090  -0.0144   1.0000   0.1102
 -11.000  -1.1848   0.01649   0.01053  -0.0127   1.0000   0.1139
 -10.750  -1.1696   0.01606   0.01013  -0.0105   1.0000   0.1185
 -10.500  -1.1515   0.01578   0.00982  -0.0086   1.0000   0.1230
 -10.250  -1.1330   0.01553   0.00951  -0.0069   1.0000   0.1273
 -10.000  -1.1162   0.01519   0.00922  -0.0049   1.0000   0.1325
  -9.750  -1.0967   0.01501   0.00899  -0.0033   1.0000   0.1370
  -9.500  -1.0778   0.01474   0.00868  -0.0015   1.0000   0.1408
  -9.250  -1.0600   0.01442   0.00839   0.0004   1.0000   0.1450
  -9.000  -1.0403   0.01422   0.00815   0.0020   1.0000   0.1490
  -8.750  -1.0194   0.01408   0.00794   0.0034   1.0000   0.1525
  -8.500  -1.0007   0.01373   0.00761   0.0052   1.0000   0.1566
  -8.250  -0.9807   0.01351   0.00739   0.0067   1.0000   0.1605
  -8.000  -0.9595   0.01336   0.00720   0.0081   1.0000   0.1644
  -7.750  -0.9377   0.01326   0.00703   0.0094   1.0000   0.1674
  -7.500  -0.9182   0.01291   0.00674   0.0110   1.0000   0.1720
  -7.250  -0.8969   0.01275   0.00657   0.0123   1.0000   0.1759
  -7.000  -0.8749   0.01265   0.00643   0.0136   1.0000   0.1798
  -6.750  -0.8529   0.01251   0.00625   0.0148   1.0000   0.1829
  -6.500  -0.8322   0.01225   0.00603   0.0162   1.0000   0.1872
  -6.250  -0.8103   0.01213   0.00591   0.0174   1.0000   0.1910
  -6.000  -0.7741   0.01205   0.00581   0.0158   0.9978   0.1953
  -5.750  -0.7248   0.01186   0.00563   0.0114   0.9934   0.2005
  -5.500  -0.6823   0.01167   0.00547   0.0085   0.9885   0.2056
  -5.250  -0.6398   0.01154   0.00533   0.0056   0.9846   0.2103
  -5.000  -0.5972   0.01136   0.00515   0.0027   0.9820   0.2150
  -4.750  -0.5622   0.01111   0.00496   0.0013   0.9773   0.2200
  -4.500  -0.5226   0.01093   0.00479  -0.0009   0.9727   0.2246
  -4.250  -0.4793   0.01080   0.00462  -0.0038   0.9697   0.2289
  -4.000  -0.4417   0.01046   0.00438  -0.0057   0.9653   0.2350
  -3.750  -0.4035   0.01024   0.00418  -0.0075   0.9591   0.2401
  -3.500  -0.3608   0.01003   0.00396  -0.0102   0.9539   0.2448
  -3.250  -0.3327   0.00974   0.00374  -0.0099   0.9431   0.2505
  -3.000  -0.3016   0.00953   0.00356  -0.0102   0.9314   0.2561
  -2.750  -0.2718   0.00937   0.00337  -0.0101   0.9143   0.2609
  -2.500  -0.2432   0.00911   0.00314  -0.0098   0.8875   0.2670
  -2.250  -0.2149   0.00897   0.00290  -0.0093   0.8337   0.2736
  -2.000  -0.1909   0.00907   0.00270  -0.0079   0.7566   0.2797
  -1.750  -0.1691   0.00921   0.00261  -0.0063   0.6848   0.2867
  -1.500  -0.1464   0.00941   0.00254  -0.0050   0.6180   0.2938
  -1.250  -0.1234   0.00951   0.00248  -0.0039   0.5593   0.3026
  -1.000  -0.0993   0.00965   0.00244  -0.0029   0.5084   0.3126
  -0.750  -0.0750   0.00971   0.00241  -0.0021   0.4665   0.3245
  -0.500  -0.0502   0.00977   0.00238  -0.0014   0.4311   0.3379
  -0.250  -0.0251   0.00980   0.00237  -0.0007   0.4008   0.3545
   0.000   0.0000   0.00982   0.00236   0.0000   0.3754   0.3753
   0.250   0.0251   0.00980   0.00237   0.0007   0.3544   0.4007
   0.500   0.0502   0.00977   0.00238   0.0014   0.3379   0.4311
   0.750   0.0749   0.00971   0.00241   0.0021   0.3245   0.4666
   1.000   0.0993   0.00965   0.00244   0.0029   0.3125   0.5086
   1.250   0.1234   0.00951   0.00248   0.0039   0.3027   0.5594
   1.500   0.1464   0.00941   0.00254   0.0050   0.2938   0.6182
   1.750   0.1691   0.00921   0.00261   0.0063   0.2867   0.6848
   2.000   0.1909   0.00907   0.00270   0.0079   0.2798   0.7566
   2.250   0.2149   0.00897   0.00290   0.0093   0.2736   0.8337
   2.500   0.2432   0.00910   0.00314   0.0098   0.2670   0.8878
   2.750   0.2718   0.00937   0.00337   0.0101   0.2609   0.9143
   3.000   0.3016   0.00952   0.00356   0.0102   0.2561   0.9313
   3.250   0.3327   0.00974   0.00374   0.0099   0.2504   0.9431
   3.500   0.3607   0.01003   0.00396   0.0102   0.2448   0.9539
   3.750   0.4032   0.01023   0.00418   0.0076   0.2401   0.9590
   4.000   0.4415   0.01046   0.00438   0.0057   0.2350   0.9652
   4.250   0.4793   0.01080   0.00462   0.0038   0.2290   0.9697
   4.500   0.5228   0.01093   0.00479   0.0008   0.2247   0.9728
   4.750   0.5623   0.01111   0.00496  -0.0014   0.2200   0.9774
   5.000   0.5973   0.01136   0.00515  -0.0027   0.2150   0.9820
   5.250   0.6390   0.01154   0.00533  -0.0055   0.2103   0.9845
   5.500   0.6823   0.01167   0.00547  -0.0085   0.2057   0.9886
   5.750   0.7247   0.01186   0.00563  -0.0114   0.2006   0.9934
   6.000   0.7742   0.01205   0.00581  -0.0158   0.1953   0.9978
   6.250   0.8102   0.01212   0.00591  -0.0174   0.1909   1.0000
   6.500   0.8321   0.01225   0.00603  -0.0162   0.1871   1.0000
   6.750   0.8529   0.01251   0.00625  -0.0148   0.1829   1.0000
   7.000   0.8749   0.01263   0.00642  -0.0136   0.1796   1.0000
   7.250   0.8968   0.01275   0.00657  -0.0123   0.1759   1.0000
   7.500   0.9181   0.01292   0.00674  -0.0110   0.1721   1.0000
   7.750   0.9376   0.01325   0.00702  -0.0094   0.1674   1.0000
   8.000   0.9595   0.01336   0.00720  -0.0081   0.1644   1.0000
   8.250   0.9806   0.01351   0.00739  -0.0067   0.1605   1.0000
   8.500   1.0007   0.01373   0.00761  -0.0052   0.1566   1.0000
   8.750   1.0193   0.01407   0.00793  -0.0034   0.1525   1.0000
   9.000   1.0402   0.01421   0.00815  -0.0020   0.1490   1.0000
   9.250   1.0600   0.01442   0.00838  -0.0004   0.1450   1.0000
   9.500   1.0778   0.01474   0.00868   0.0015   0.1408   1.0000
   9.750   1.0966   0.01500   0.00899   0.0033   0.1370   1.0000
  10.000   1.1161   0.01519   0.00922   0.0049   0.1325   1.0000
  10.250   1.1330   0.01552   0.00951   0.0069   0.1273   1.0000
  10.500   1.1515   0.01578   0.00982   0.0086   0.1230   1.0000
  10.750   1.1696   0.01605   0.01013   0.0105   0.1185   1.0000
  11.000   1.1849   0.01648   0.01053   0.0126   0.1140   1.0000
  11.250   1.2029   0.01678   0.01089   0.0144   0.1102   1.0000
  11.500   1.2200   0.01713   0.01127   0.0163   0.1058   1.0000
  11.750   1.2337   0.01766   0.01176   0.0186   0.1011   1.0000
  12.000   1.2513   0.01798   0.01217   0.0204   0.0974   1.0000
  12.250   1.2666   0.01842   0.01263   0.0225   0.0930   1.0000
  12.500   1.2790   0.01901   0.01321   0.0248   0.0885   1.0000
  12.750   1.2945   0.01943   0.01369   0.0268   0.0846   1.0000
  13.000   1.3036   0.02002   0.01428   0.0297   0.0804   1.0000
  13.250   1.3130   0.02061   0.01492   0.0324   0.0767   1.0000
  13.500   1.3234   0.02122   0.01556   0.0349   0.0728   1.0000
  13.750   1.3290   0.02210   0.01644   0.0377   0.0690   1.0000
  14.000   1.3394   0.02280   0.01722   0.0398   0.0654   1.0000
  14.250   1.3457   0.02376   0.01820   0.0421   0.0620   1.0000
  14.500   1.3487   0.02495   0.01944   0.0445   0.0588   1.0000
  14.750   1.3550   0.02604   0.02060   0.0463   0.0556   1.0000
  15.000   1.3550   0.02762   0.02222   0.0481   0.0527   1.0000
  15.250   1.3542   0.02943   0.02411   0.0495   0.0501   1.0000
  15.500   1.3534   0.03146   0.02623   0.0504   0.0478   1.0000
  15.750   1.3464   0.03436   0.02920   0.0504   0.0456   1.0000
  16.000   1.3328   0.03845   0.03339   0.0493   0.0440   1.0000
  16.250   1.3255   0.04231   0.03741   0.0478   0.0424   1.0000
  16.500   1.3099   0.04761   0.04284   0.0451   0.0411   1.0000
  16.750   1.2875   0.05404   0.04942   0.0418   0.0405   1.0000
  17.000   1.2592   0.06135   0.05687   0.0380   0.0398   1.0000
  17.250   1.2304   0.06866   0.06431   0.0344   0.0395   1.0000
  17.500   1.2004   0.07614   0.07191   0.0307   0.0392   1.0000
  17.750   1.1709   0.08373   0.07960   0.0269   0.0387   1.0000
<< Back to E474 (14.09%) (e474-il)

Polar data table (+)

Polar graphs


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