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EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 748 AIRFOIL (e748-il)
Reynolds number: 50,000
Max Cl/Cd: 12.37 at α=-2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e748-il-50000.txt
Download as CSV file: xf-e748-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 748 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2847   0.11799   0.11135  -0.0431   1.0000   0.1756
 -10.250  -0.3199   0.11008   0.10359  -0.0461   1.0000   0.1627
 -10.000  -0.4839   0.08268   0.07646  -0.0606   1.0000   0.1343
  -9.750  -0.5180   0.07808   0.07197  -0.0600   1.0000   0.1332
  -9.500  -0.5577   0.07421   0.06820  -0.0585   1.0000   0.1314
  -9.250  -0.6109   0.07079   0.06487  -0.0564   1.0000   0.1289
  -9.000  -0.6996   0.06305   0.05679  -0.0610   1.0000   0.1232
  -8.750  -0.7184   0.05926   0.05275  -0.0618   1.0000   0.1233
  -8.500  -0.7208   0.05667   0.05005  -0.0614   1.0000   0.1249
  -8.250  -0.7205   0.05401   0.04722  -0.0615   1.0000   0.1269
  -8.000  -0.7168   0.05131   0.04426  -0.0621   1.0000   0.1299
  -7.750  -0.7090   0.04826   0.04065  -0.0640   1.0000   0.1344
  -7.500  -0.6901   0.04716   0.03986  -0.0635   0.9970   0.1424
  -7.250  -0.6460   0.04513   0.03778  -0.0683   0.9850   0.1582
  -7.000  -0.6064   0.04310   0.03581  -0.0725   0.9733   0.1832
  -6.750  -0.5704   0.04205   0.03532  -0.0752   0.9610   0.2226
  -6.500  -0.5346   0.04519   0.03927  -0.0730   0.9467   0.2709
  -6.250  -0.4908   0.05319   0.04751  -0.0663   0.9314   0.3095
  -6.000  -0.4155   0.06812   0.06241  -0.0512   0.9162   0.3317
  -5.750  -0.3837   0.07033   0.06447  -0.0494   0.9031   0.3604
  -5.500  -0.3528   0.07203   0.06600  -0.0476   0.8912   0.3890
  -5.250  -0.2933   0.07425   0.06797  -0.0467   0.8819   0.4249
  -5.000  -0.2957   0.07349   0.06714  -0.0450   0.8689   0.4456
  -4.750  -0.1492   0.07743   0.07069  -0.0438   0.8634   0.5335
  -4.500  -0.1754   0.07628   0.06954  -0.0402   0.8504   0.5344
  -4.250  -0.1803   0.07602   0.06926  -0.0367   0.8394   0.5593
  -3.250   0.5238   0.04548   0.03689  -0.1253   0.8297   1.0000
  -3.000   0.5336   0.04543   0.03679  -0.1246   0.8160   1.0000
  -2.750   0.5547   0.04483   0.03610  -0.1260   0.8055   1.0000
  -2.500  -0.1451   0.07046   0.06316  -0.0239   0.7784   0.6674
  -2.250  -0.1417   0.06923   0.06183  -0.0243   0.7718   0.6673
  -2.000  -0.1611   0.06892   0.06152  -0.0210   0.7644   0.6645
  -1.750  -0.1511   0.06781   0.06028  -0.0232   0.7584   0.6675
  -1.500  -0.1452   0.06738   0.05979  -0.0216   0.7522   0.6723
  -1.250  -0.1510   0.06716   0.05953  -0.0207   0.7461   0.6736
  -1.000  -0.1310   0.06662   0.05887  -0.0224   0.7405   0.6780
  -0.750  -0.1101   0.06630   0.05842  -0.0251   0.7352   0.6820
  -0.500  -0.1119   0.06658   0.05865  -0.0256   0.7305   0.6830
  -0.250  -0.0913   0.06664   0.05859  -0.0292   0.7251   0.6858
   0.000  -0.0618   0.06641   0.05827  -0.0306   0.7200   0.6902
   0.250  -0.0485   0.06695   0.05873  -0.0321   0.7167   0.6921
   0.500  -0.0429   0.06774   0.05948  -0.0331   0.7143   0.6937
   0.750  -0.0308   0.06855   0.06024  -0.0350   0.7124   0.6957
   1.000  -0.0151   0.06957   0.06120  -0.0376   0.7125   0.6976
   1.250   0.0042   0.07079   0.06236  -0.0408   0.7144   0.6995
   1.500   0.0279   0.07218   0.06367  -0.0446   0.7162   0.7018
   1.750  -0.0752   0.07640   0.06830  -0.0396   0.8457   0.6980
   2.000  -0.0548   0.07668   0.06851  -0.0420   0.8346   0.7005
   2.250  -0.0102   0.07923   0.07091  -0.0485   0.8282   0.7032
   2.500   0.0072   0.07939   0.07103  -0.0503   0.8158   0.7047
   2.750   0.0442   0.08195   0.07351  -0.0540   0.8104   0.7080
   3.000   0.0509   0.08171   0.07326  -0.0538   0.7989   0.7099
   3.250   0.0968   0.08494   0.07640  -0.0593   0.7925   0.7132
   3.500   0.1031   0.08472   0.07615  -0.0593   0.7800   0.7144
   3.750   0.1524   0.08840   0.07973  -0.0655   0.7740   0.7180
   4.000   0.1553   0.08815   0.07947  -0.0653   0.7619   0.7200
   4.250   0.2013   0.09170   0.08295  -0.0706   0.7558   0.7239
   4.500   0.2023   0.09155   0.08281  -0.0697   0.7432   0.7256
   4.750   0.2473   0.09526   0.08648  -0.0743   0.7372   0.7293
   5.000   0.2462   0.09515   0.08639  -0.0736   0.7253   0.7309
   5.250   0.2905   0.09885   0.09003  -0.0784   0.7191   0.7356
   5.500   0.2931   0.09925   0.09043  -0.0784   0.7067   0.7382
   5.750   0.3357   0.10299   0.09414  -0.0824   0.7005   0.7434
   6.000   0.3318   0.10317   0.09435  -0.0814   0.6892   0.7458
   6.250   0.3703   0.10661   0.09777  -0.0849   0.6826   0.7512
   6.500   0.3721   0.10749   0.09867  -0.0849   0.6715   0.7541
   6.750   0.4117   0.11107   0.10222  -0.0888   0.6643   0.7595
   7.000   0.4100   0.11195   0.10315  -0.0881   0.6544   0.7627
   7.250   0.4406   0.11488   0.10609  -0.0905   0.6468   0.7695
   7.500   0.4474   0.11671   0.10794  -0.0913   0.6380   0.7746
   7.750   0.4731   0.11922   0.11049  -0.0928   0.6290   0.7816
   8.000   0.4859   0.12177   0.11308  -0.0939   0.6229   0.7881
   8.250   0.5020   0.12368   0.11503  -0.0952   0.6122   0.7950
   8.500   0.5432   0.12856   0.11997  -0.0982   0.6077   0.8064
   8.750   0.5308   0.12825   0.11971  -0.0974   0.5954   0.8108
   9.000   0.5652   0.13227   0.12380  -0.0993   0.5901   0.8249
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