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

E182 (8.47%) (e182-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E182 (8.47%) (e182-il)
Reynolds number: 100,000
Max Cl/Cd: 47.03 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e182-il-100000-n5.txt
Download as CSV file: xf-e182-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E182 (8.47%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5797   0.08795   0.08353   0.0049   1.0000   0.0255
  -8.250  -0.5818   0.08293   0.07858   0.0012   1.0000   0.0249
  -8.000  -0.5864   0.07751   0.07322  -0.0035   1.0000   0.0243
  -7.750  -0.5883   0.07109   0.06678  -0.0089   1.0000   0.0234
  -7.250  -0.5918   0.05377   0.04882  -0.0184   1.0000   0.0210
  -7.000  -0.5840   0.04882   0.04352  -0.0195   1.0000   0.0211
  -6.750  -0.5734   0.04447   0.03890  -0.0201   1.0000   0.0215
  -6.500  -0.5571   0.04167   0.03596  -0.0205   1.0000   0.0223
  -6.250  -0.5399   0.03841   0.03234  -0.0207   1.0000   0.0229
  -6.000  -0.5219   0.03451   0.02793  -0.0205   1.0000   0.0228
  -5.750  -0.5016   0.03099   0.02385  -0.0202   1.0000   0.0226
  -5.500  -0.4772   0.02813   0.02051  -0.0202   0.9810   0.0226
  -5.250  -0.4442   0.02560   0.01751  -0.0216   0.9505   0.0229
  -5.000  -0.4137   0.02364   0.01518  -0.0221   0.9296   0.0234
  -4.750  -0.3866   0.02209   0.01335  -0.0218   0.9112   0.0242
  -4.500  -0.3615   0.02081   0.01182  -0.0210   0.8950   0.0251
  -4.250  -0.3374   0.01987   0.01067  -0.0200   0.8804   0.0273
  -4.000  -0.3145   0.01889   0.00960  -0.0190   0.8672   0.0302
  -3.750  -0.2911   0.01811   0.00869  -0.0180   0.8553   0.0332
  -3.500  -0.2675   0.01739   0.00775  -0.0168   0.8444   0.0372
  -3.250  -0.2438   0.01656   0.00683  -0.0157   0.8339   0.0477
  -3.000  -0.2203   0.01564   0.00616  -0.0149   0.8237   0.0985
  -2.750  -0.1987   0.01459   0.00582  -0.0142   0.8147   0.2366
  -2.500  -0.1774   0.01359   0.00556  -0.0132   0.8058   0.4125
  -2.250  -0.1553   0.01276   0.00535  -0.0118   0.7972   0.5871
  -2.000  -0.1263   0.01212   0.00528  -0.0106   0.7900   0.7804
  -1.750  -0.0603   0.01201   0.00514  -0.0169   0.7832   0.9244
  -1.500  -0.0110   0.01206   0.00491  -0.0209   0.7762   0.9759
  -1.250   0.0352   0.01202   0.00464  -0.0248   0.7684   1.0000
  -1.000   0.0586   0.01206   0.00448  -0.0240   0.7610   1.0000
  -0.750   0.0835   0.01210   0.00437  -0.0236   0.7525   1.0000
  -0.500   0.1072   0.01216   0.00427  -0.0228   0.7459   1.0000
  -0.250   0.1326   0.01224   0.00424  -0.0224   0.7376   1.0000
   0.000   0.1567   0.01232   0.00418  -0.0217   0.7313   1.0000
   0.250   0.1824   0.01242   0.00421  -0.0214   0.7232   1.0000
   0.500   0.2069   0.01251   0.00420  -0.0207   0.7171   1.0000
   0.750   0.2328   0.01263   0.00428  -0.0204   0.7091   1.0000
   1.000   0.2575   0.01274   0.00432  -0.0197   0.7029   1.0000
   1.250   0.2834   0.01288   0.00445  -0.0195   0.6951   1.0000
   1.500   0.3084   0.01300   0.00452  -0.0188   0.6888   1.0000
   1.750   0.3343   0.01315   0.00468  -0.0185   0.6808   1.0000
   2.000   0.3593   0.01328   0.00480  -0.0179   0.6741   1.0000
   2.250   0.3851   0.01344   0.00499  -0.0175   0.6653   1.0000
   2.500   0.4101   0.01355   0.00510  -0.0168   0.6577   1.0000
   2.750   0.4356   0.01369   0.00529  -0.0163   0.6477   1.0000
   3.000   0.4609   0.01381   0.00549  -0.0158   0.6377   1.0000
   3.250   0.4859   0.01391   0.00561  -0.0150   0.6275   1.0000
   3.500   0.5109   0.01399   0.00575  -0.0143   0.6160   1.0000
   3.750   0.5362   0.01408   0.00594  -0.0136   0.6027   1.0000
   4.000   0.5613   0.01415   0.00610  -0.0129   0.5884   1.0000
   4.250   0.5864   0.01421   0.00625  -0.0121   0.5728   1.0000
   4.500   0.6116   0.01429   0.00645  -0.0114   0.5537   1.0000
   4.750   0.6366   0.01436   0.00665  -0.0106   0.5322   1.0000
   5.000   0.6615   0.01446   0.00686  -0.0099   0.5063   1.0000
   5.250   0.6852   0.01457   0.00694  -0.0088   0.4594   1.0000
   5.500   0.7057   0.01511   0.00701  -0.0075   0.3519   1.0000
   5.750   0.7234   0.01648   0.00768  -0.0067   0.2312   1.0000
   6.000   0.7402   0.01815   0.00871  -0.0062   0.1244   1.0000
   6.250   0.7577   0.01972   0.00983  -0.0054   0.0552   1.0000
   6.500   0.7762   0.02112   0.01108  -0.0044   0.0332   1.0000
   6.750   0.7958   0.02229   0.01234  -0.0034   0.0280   1.0000
   7.000   0.8143   0.02356   0.01373  -0.0024   0.0257   1.0000
   7.250   0.8325   0.02480   0.01519  -0.0013   0.0240   1.0000
   7.500   0.8499   0.02615   0.01669  -0.0001   0.0228   1.0000
   7.750   0.8669   0.02759   0.01823   0.0011   0.0218   1.0000
   8.000   0.8837   0.02911   0.01983   0.0023   0.0208   1.0000
   8.250   0.9000   0.03093   0.02170   0.0034   0.0197   1.0000
   8.500   0.9186   0.03254   0.02355   0.0045   0.0187   1.0000
   8.750   0.9364   0.03448   0.02572   0.0055   0.0179   1.0000
   9.000   0.9533   0.03675   0.02826   0.0066   0.0176   1.0000
   9.250   0.9680   0.03927   0.03113   0.0078   0.0174   1.0000
   9.500   0.9793   0.04212   0.03434   0.0090   0.0172   1.0000
   9.750   0.9867   0.04512   0.03769   0.0103   0.0171   1.0000
  10.000   0.9889   0.04838   0.04132   0.0116   0.0171   1.0000
  10.250   0.9858   0.05170   0.04499   0.0130   0.0171   1.0000
  10.500   0.9761   0.05495   0.04851   0.0144   0.0172   1.0000
  10.750   0.9634   0.05862   0.05243   0.0149   0.0173   1.0000
  11.000   0.9485   0.06276   0.05681   0.0143   0.0173   1.0000
  11.250   0.9325   0.06746   0.06172   0.0127   0.0174   1.0000
  11.500   0.9146   0.07290   0.06735   0.0101   0.0175   1.0000
  11.750   0.8945   0.07932   0.07394   0.0062   0.0176   1.0000
  12.000   0.8739   0.08672   0.08148   0.0013   0.0178   1.0000
  12.250   0.8525   0.09545   0.09031  -0.0047   0.0181   1.0000
<< Back to E182 (8.47%) (e182-il)

Polar data table (+)

Polar graphs


<< Back to E182 (8.47%) (e182-il)