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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 500,000
Max Cl/Cd: 153.74 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e471-il-500000.txt
Download as CSV file: xf-e471-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E471  (6.25%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3681   0.11494   0.11272  -0.0247   1.0000   0.0108
  -9.000  -0.3697   0.11282   0.11063  -0.0242   1.0000   0.0109
  -8.750  -0.3732   0.11094   0.10878  -0.0235   1.0000   0.0110
  -8.500  -0.3635   0.10757   0.10542  -0.0263   0.9988   0.0111
  -8.250  -0.3485   0.10353   0.10138  -0.0307   0.9968   0.0112
  -8.000  -0.3326   0.09946   0.09731  -0.0352   0.9949   0.0112
  -7.750  -0.3190   0.09550   0.09336  -0.0392   0.9919   0.0112
  -7.500  -0.3047   0.09160   0.08946  -0.0434   0.9883   0.0112
  -7.250  -0.2975   0.08604   0.08391  -0.0454   0.9862   0.0123
  -7.000  -0.2788   0.08267   0.08054  -0.0497   0.9839   0.0128
  -6.750  -0.2640   0.07916   0.07703  -0.0535   0.9786   0.0132
  -6.500  -0.2415   0.07487   0.07274  -0.0598   0.9744   0.0138
  -6.250  -0.2140   0.07029   0.06815  -0.0678   0.9719   0.0144
  -6.000  -0.1838   0.06541   0.06325  -0.0767   0.9693   0.0153
  -5.750  -0.1603   0.06094   0.05875  -0.0836   0.9624   0.0163
  -5.500  -0.1111   0.05520   0.05294  -0.0970   0.9599   0.0180
  -5.250  -0.0633   0.04876   0.04637  -0.1095   0.9584   0.0183
  -5.000  -0.0244   0.03772   0.03508  -0.1233   0.9529   0.0193
  -4.750   0.0051   0.03526   0.03254  -0.1271   0.9499   0.0209
  -4.500   0.0453   0.03149   0.02858  -0.1331   0.9483   0.0235
  -4.250   0.0940   0.02910   0.02573  -0.1379   0.9472   0.0283
  -3.250   0.2601   0.01419   0.00917  -0.1550   0.9450   0.0263
  -3.000   0.2983   0.01249   0.00719  -0.1571   0.9443   0.0253
  -2.750   0.3233   0.01170   0.00629  -0.1564   0.9383   0.0258
  -2.500   0.3584   0.01059   0.00505  -0.1578   0.9364   0.0243
  -2.250   0.3940   0.00980   0.00416  -0.1594   0.9347   0.0237
  -2.000   0.4300   0.00922   0.00350  -0.1610   0.9330   0.0240
  -1.750   0.4661   0.00877   0.00299  -0.1627   0.9314   0.0258
  -1.500   0.4930   0.00854   0.00270  -0.1623   0.9251   0.0283
  -1.250   0.5269   0.00808   0.00238  -0.1636   0.9214   0.0830
  -1.000   0.5622   0.00747   0.00222  -0.1655   0.9184   0.2459
  -0.750   0.5906   0.00708   0.00220  -0.1658   0.9114   0.3896
  -0.500   0.6231   0.00656   0.00218  -0.1669   0.9062   0.5821
  -0.250   0.6494   0.00612   0.00224  -0.1665   0.8989   0.7702
   0.000   0.6686   0.00566   0.00208  -0.1638   0.8916   1.0000
   0.250   0.6960   0.00568   0.00204  -0.1636   0.8825   1.0000
   0.500   0.7252   0.00570   0.00199  -0.1637   0.8744   1.0000
   0.750   0.7536   0.00572   0.00196  -0.1637   0.8654   1.0000
   1.000   0.7809   0.00577   0.00196  -0.1635   0.8552   1.0000
   1.250   0.8086   0.00582   0.00197  -0.1633   0.8448   1.0000
   1.500   0.8364   0.00588   0.00198  -0.1631   0.8344   1.0000
   1.750   0.8637   0.00595   0.00202  -0.1629   0.8232   1.0000
   2.000   0.8904   0.00602   0.00207  -0.1625   0.8103   1.0000
   2.250   0.9169   0.00611   0.00213  -0.1621   0.7964   1.0000
   2.500   0.9432   0.00621   0.00219  -0.1616   0.7808   1.0000
   2.750   0.9689   0.00632   0.00228  -0.1610   0.7625   1.0000
   3.000   0.9944   0.00647   0.00239  -0.1604   0.7416   1.0000
   3.250   1.0193   0.00663   0.00251  -0.1596   0.7166   1.0000
   3.500   1.0429   0.00688   0.00264  -0.1586   0.6822   1.0000
   3.750   1.0635   0.00730   0.00283  -0.1570   0.6248   1.0000
   4.000   1.0787   0.00814   0.00316  -0.1544   0.5246   1.0000
   4.250   1.0938   0.00916   0.00367  -0.1521   0.4204   1.0000
   4.500   1.1122   0.01004   0.00414  -0.1504   0.3387   1.0000
   4.750   1.1290   0.01114   0.00471  -0.1487   0.2400   1.0000
   5.500   1.1823   0.01452   0.00678  -0.1440   0.0223   1.0000
   5.750   1.2035   0.01534   0.00760  -0.1427   0.0115   1.0000
   6.000   1.2250   0.01614   0.00852  -0.1413   0.0099   1.0000
   6.250   1.2441   0.01723   0.00979  -0.1396   0.0094   1.0000
   6.500   1.2633   0.01826   0.01093  -0.1379   0.0092   1.0000
   6.750   1.2835   0.01911   0.01187  -0.1365   0.0088   1.0000
   7.000   1.3033   0.02000   0.01285  -0.1351   0.0082   1.0000
   7.250   1.3211   0.02122   0.01422  -0.1333   0.0079   1.0000
   7.500   1.3386   0.02261   0.01574  -0.1314   0.0077   1.0000
   7.750   1.3564   0.02419   0.01746  -0.1296   0.0074   1.0000
   8.000   1.3748   0.02606   0.01949  -0.1279   0.0072   1.0000
   8.250   1.3942   0.02863   0.02231  -0.1263   0.0072   1.0000
   8.500   1.4137   0.03286   0.02697  -0.1245   0.0079   1.0000
   8.750   1.3753   0.04134   0.03726  -0.1106   0.0191   1.0000
   9.000   1.3768   0.04504   0.04120  -0.1075   0.0184   1.0000
   9.250   1.3749   0.04869   0.04505  -0.1041   0.0178   1.0000
   9.500   1.3701   0.05229   0.04881  -0.1007   0.0173   1.0000
   9.750   1.3567   0.05572   0.05240  -0.0960   0.0170   1.0000
  10.000   1.3415   0.05919   0.05600  -0.0917   0.0168   1.0000
  10.250   1.3186   0.06337   0.06036  -0.0874   0.0166   1.0000
  10.500   1.2943   0.06798   0.06516  -0.0839   0.0166   1.0000
  10.750   1.2671   0.07339   0.07077  -0.0814   0.0166   1.0000
  11.000   1.2377   0.07937   0.07694  -0.0801   0.0167   1.0000
  11.250   1.1983   0.08672   0.08454  -0.0804   0.0169   1.0000
  11.500   1.1442   0.09630   0.09442  -0.0833   0.0174   1.0000
  11.750   1.0864   0.10814   0.10653  -0.0901   0.0185   1.0000
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