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

EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 403 AIRFOIL (e403-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.34 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e403-il-1000000-n5.txt
Download as CSV file: xf-e403-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 403 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.5715   0.07511   0.07267  -0.1153   0.9786   0.0048
 -15.250  -0.5735   0.06976   0.06724  -0.1196   0.9774   0.0049
 -15.000  -0.5959   0.06119   0.05845  -0.1259   0.9762   0.0049
 -14.750  -0.6016   0.05569   0.05279  -0.1306   0.9752   0.0049
 -14.500  -0.6029   0.05103   0.04798  -0.1348   0.9743   0.0049
 -14.250  -0.6105   0.04553   0.04225  -0.1394   0.9734   0.0049
 -14.000  -0.6106   0.04229   0.03888  -0.1414   0.9703   0.0049
 -13.750  -0.6075   0.03946   0.03591  -0.1432   0.9671   0.0050
 -13.500  -0.6012   0.03678   0.03308  -0.1453   0.9647   0.0050
 -13.250  -0.5932   0.03420   0.03034  -0.1474   0.9624   0.0050
 -13.000  -0.5802   0.03216   0.02817  -0.1495   0.9604   0.0051
 -12.750  -0.5692   0.03063   0.02653  -0.1502   0.9573   0.0052
 -12.500  -0.5598   0.02922   0.02502  -0.1502   0.9531   0.0052
 -12.250  -0.5493   0.02755   0.02322  -0.1505   0.9495   0.0054
 -12.000  -0.5346   0.02622   0.02178  -0.1511   0.9468   0.0054
 -11.750  -0.5226   0.02500   0.02045  -0.1509   0.9438   0.0054
 -11.500  -0.5138   0.02384   0.01919  -0.1498   0.9402   0.0056
 -11.250  -0.5009   0.02287   0.01814  -0.1492   0.9368   0.0057
 -11.000  -0.4875   0.02182   0.01699  -0.1487   0.9338   0.0057
 -10.750  -0.4715   0.02094   0.01602  -0.1484   0.9313   0.0059
 -10.500  -0.4583   0.02021   0.01523  -0.1474   0.9287   0.0060
 -10.250  -0.4475   0.01935   0.01431  -0.1460   0.9257   0.0060
 -10.000  -0.4356   0.01855   0.01345  -0.1448   0.9226   0.0060
  -9.750  -0.4204   0.01787   0.01271  -0.1439   0.9200   0.0061
  -9.500  -0.4008   0.01744   0.01221  -0.1436   0.9180   0.0063
  -9.250  -0.3887   0.01664   0.01136  -0.1423   0.9154   0.0063
  -9.000  -0.3794   0.01601   0.01069  -0.1402   0.9125   0.0063
  -8.750  -0.3762   0.01515   0.00977  -0.1375   0.9088   0.0065
  -8.500  -0.3617   0.01442   0.00900  -0.1367   0.9063   0.0067
  -8.250  -0.3422   0.01380   0.00834  -0.1367   0.9043   0.0069
  -8.000  -0.3198   0.01329   0.00778  -0.1369   0.9024   0.0070
  -7.750  -0.2973   0.01283   0.00728  -0.1370   0.9006   0.0072
  -7.500  -0.2754   0.01242   0.00685  -0.1367   0.8990   0.0074
  -7.250  -0.2523   0.01203   0.00644  -0.1366   0.8972   0.0076
  -7.000  -0.2281   0.01166   0.00603  -0.1367   0.8954   0.0079
  -6.750  -0.2029   0.01130   0.00565  -0.1369   0.8936   0.0081
  -6.500  -0.1767   0.01100   0.00531  -0.1372   0.8921   0.0085
  -6.250  -0.1497   0.01073   0.00503  -0.1376   0.8906   0.0088
  -6.000  -0.1226   0.01036   0.00462  -0.1382   0.8892   0.0094
  -5.750  -0.0944   0.01007   0.00430  -0.1388   0.8878   0.0099
  -5.500  -0.0655   0.00983   0.00404  -0.1396   0.8865   0.0105
  -5.250  -0.0382   0.00963   0.00382  -0.1399   0.8850   0.0113
  -5.000  -0.0109   0.00944   0.00362  -0.1402   0.8834   0.0120
  -4.750   0.0169   0.00922   0.00341  -0.1407   0.8817   0.0145
  -4.500   0.0452   0.00882   0.00314  -0.1414   0.8799   0.0448
  -4.250   0.0743   0.00827   0.00284  -0.1426   0.8782   0.1094
  -4.000   0.1045   0.00769   0.00254  -0.1441   0.8766   0.1899
  -3.750   0.1360   0.00698   0.00220  -0.1460   0.8751   0.2982
  -3.500   0.1698   0.00610   0.00184  -0.1486   0.8737   0.4526
  -3.250   0.2013   0.00589   0.00177  -0.1498   0.8721   0.5070
  -3.000   0.2308   0.00582   0.00177  -0.1503   0.8700   0.5358
  -2.750   0.2592   0.00579   0.00177  -0.1506   0.8669   0.5493
  -2.500   0.2880   0.00577   0.00172  -0.1509   0.8631   0.5570
  -2.250   0.3177   0.00572   0.00166  -0.1514   0.8591   0.5622
  -2.000   0.3467   0.00570   0.00162  -0.1517   0.8548   0.5663
  -1.750   0.3746   0.00568   0.00159  -0.1518   0.8494   0.5693
  -1.500   0.4038   0.00567   0.00153  -0.1522   0.8446   0.5719
  -1.250   0.4327   0.00565   0.00150  -0.1525   0.8401   0.5742
  -1.000   0.4609   0.00564   0.00150  -0.1528   0.8351   0.5766
  -0.750   0.4898   0.00564   0.00148  -0.1531   0.8301   0.5791
  -0.500   0.5183   0.00564   0.00148  -0.1533   0.8249   0.5815
  -0.250   0.5465   0.00565   0.00148  -0.1535   0.8184   0.5840
   0.000   0.5748   0.00567   0.00147  -0.1537   0.8115   0.5863
   0.250   0.6024   0.00570   0.00147  -0.1537   0.8015   0.5882
   0.500   0.6292   0.00573   0.00148  -0.1536   0.7879   0.5903
   0.750   0.6550   0.00581   0.00150  -0.1532   0.7708   0.5925
   1.000   0.6799   0.00592   0.00154  -0.1527   0.7510   0.5947
   1.250   0.7024   0.00609   0.00161  -0.1516   0.7247   0.5968
   1.500   0.7225   0.00633   0.00172  -0.1500   0.6929   0.5990
   1.750   0.7399   0.00665   0.00187  -0.1479   0.6543   0.6012
   2.000   0.7560   0.00701   0.00204  -0.1456   0.6164   0.6031
   2.250   0.7725   0.00735   0.00223  -0.1434   0.5785   0.6050
   2.500   0.7867   0.00771   0.00243  -0.1407   0.5396   0.6069
   2.750   0.8011   0.00809   0.00266  -0.1381   0.4999   0.6089
   3.000   0.8180   0.00846   0.00288  -0.1361   0.4643   0.6111
   3.250   0.8369   0.00880   0.00310  -0.1345   0.4340   0.6132
   3.500   0.8568   0.00914   0.00333  -0.1331   0.4064   0.6152
   3.750   0.8765   0.00951   0.00357  -0.1317   0.3763   0.6170
   4.000   0.8950   0.00995   0.00384  -0.1301   0.3388   0.6188
   4.250   0.9134   0.01041   0.00413  -0.1286   0.3022   0.6207
   4.500   0.9313   0.01093   0.00447  -0.1269   0.2594   0.6227
   4.750   0.9501   0.01142   0.00480  -0.1255   0.2246   0.6247
   5.000   0.9690   0.01193   0.00515  -0.1241   0.1895   0.6266
   5.250   0.9877   0.01246   0.00551  -0.1227   0.1563   0.6285
   5.500   1.0073   0.01293   0.00587  -0.1215   0.1307   0.6304
   5.750   1.0266   0.01344   0.00625  -0.1202   0.1061   0.6323
   6.000   1.0463   0.01393   0.00663  -0.1190   0.0855   0.6341
   6.250   1.0662   0.01441   0.00703  -0.1178   0.0668   0.6359
   6.500   1.0846   0.01499   0.00751  -0.1165   0.0459   0.6379
   6.750   1.1030   0.01558   0.00802  -0.1151   0.0296   0.6398
   7.000   1.1203   0.01626   0.00860  -0.1135   0.0128   0.6416
   7.250   1.1406   0.01672   0.00907  -0.1125   0.0101   0.6436
   7.500   1.1613   0.01713   0.00951  -0.1115   0.0091   0.6455
   7.750   1.1816   0.01757   0.00997  -0.1104   0.0085   0.6475
   8.000   1.2013   0.01804   0.01047  -0.1093   0.0080   0.6495
   8.250   1.2207   0.01854   0.01100  -0.1082   0.0076   0.6512
   8.500   1.2397   0.01909   0.01160  -0.1070   0.0072   0.6533
   8.750   1.2590   0.01959   0.01215  -0.1058   0.0070   0.6553
   9.000   1.2777   0.02012   0.01274  -0.1047   0.0068   0.6572
   9.250   1.2961   0.02069   0.01336  -0.1034   0.0067   0.6592
   9.500   1.3142   0.02128   0.01400  -0.1022   0.0065   0.6613
   9.750   1.3315   0.02193   0.01470  -0.1009   0.0063   0.6634
  10.000   1.3483   0.02260   0.01543  -0.0995   0.0061   0.6655
  10.250   1.3647   0.02332   0.01619  -0.0981   0.0060   0.6673
  10.500   1.3809   0.02404   0.01698  -0.0967   0.0058   0.6695
  10.750   1.3959   0.02486   0.01785  -0.0952   0.0057   0.6715
  11.000   1.4102   0.02574   0.01880  -0.0936   0.0055   0.6736
  11.250   1.4226   0.02677   0.01990  -0.0919   0.0053   0.6757
  11.500   1.4326   0.02800   0.02121  -0.0898   0.0051   0.6778
  11.750   1.4440   0.02912   0.02242  -0.0880   0.0051   0.6801
  12.000   1.4562   0.03017   0.02353  -0.0864   0.0050   0.6822
  12.250   1.4682   0.03126   0.02471  -0.0849   0.0050   0.6844
  12.500   1.4787   0.03248   0.02601  -0.0832   0.0049   0.6868
  12.750   1.4888   0.03376   0.02739  -0.0816   0.0048   0.6891
  13.000   1.4977   0.03514   0.02887  -0.0799   0.0048   0.6914
  13.250   1.5061   0.03662   0.03043  -0.0783   0.0047   0.6937
  13.500   1.5133   0.03823   0.03213  -0.0767   0.0047   0.6960
  13.750   1.5197   0.03995   0.03395  -0.0751   0.0046   0.6983
  14.000   1.5252   0.04180   0.03590  -0.0736   0.0045   0.7008
  14.250   1.5301   0.04379   0.03800  -0.0722   0.0045   0.7035
  14.500   1.5339   0.04595   0.04026  -0.0709   0.0044   0.7062
  14.750   1.5370   0.04825   0.04267  -0.0697   0.0044   0.7089
  15.000   1.5391   0.05075   0.04528  -0.0687   0.0043   0.7114
  15.250   1.5404   0.05341   0.04805  -0.0678   0.0043   0.7137
  15.500   1.5405   0.05633   0.05109  -0.0671   0.0042   0.7162
  15.750   1.5399   0.05947   0.05435  -0.0667   0.0042   0.7189
  16.000   1.5383   0.06286   0.05787  -0.0665   0.0041   0.7219
  16.250   1.5358   0.06651   0.06164  -0.0666   0.0041   0.7250
  16.500   1.5318   0.07050   0.06575  -0.0669   0.0041   0.7279
  17.000   1.5214   0.07939   0.07491  -0.0687   0.0040   0.7338
  17.250   1.5141   0.08443   0.08008  -0.0701   0.0040   0.7369
  17.500   1.5060   0.08978   0.08557  -0.0719   0.0040   0.7399
  17.750   1.4967   0.09549   0.09142  -0.0741   0.0039   0.7426
  18.000   1.4857   0.10167   0.09774  -0.0767   0.0039   0.7451
  18.250   1.4752   0.10794   0.10415  -0.0797   0.0039   0.7478
  18.500   1.4634   0.11462   0.11098  -0.0830   0.0039   0.7506
  18.750   1.4506   0.12159   0.11808  -0.0867   0.0039   0.7534
<< Back to EPPLER 403 AIRFOIL (e403-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 403 AIRFOIL (e403-il)