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EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 656 AIRFOIL (e656-il)
Reynolds number: 100,000
Max Cl/Cd: 29.8 at α=11.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e656-il-100000-n5.txt
Download as CSV file: xf-e656-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 656 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0931   0.10368   0.09786  -0.1082   0.8380   0.0220
 -11.500  -0.0899   0.09975   0.09390  -0.1102   0.8339   0.0219
 -11.250  -0.0880   0.09589   0.09006  -0.1119   0.8293   0.0219
 -11.000  -0.0899   0.09117   0.08537  -0.1142   0.8250   0.0220
 -10.750  -0.0847   0.08817   0.08235  -0.1156   0.8211   0.0216
 -10.500  -0.0890   0.08291   0.07710  -0.1184   0.8179   0.0217
 -10.250  -0.0938   0.07792   0.07214  -0.1210   0.8144   0.0216
 -10.000  -0.0989   0.07301   0.06728  -0.1236   0.8106   0.0213
  -9.500  -0.1922   0.05127   0.04511  -0.1368   0.8017   0.0186
  -9.250  -0.2108   0.04832   0.04197  -0.1358   0.7978   0.0186
  -9.000  -0.2051   0.04809   0.04182  -0.1345   0.7937   0.0195
  -8.750  -0.2356   0.04370   0.03689  -0.1314   0.7890   0.0188
  -8.500  -0.2310   0.04215   0.03519  -0.1301   0.7857   0.0191
  -8.250  -0.2234   0.04079   0.03365  -0.1289   0.7831   0.0202
  -8.000  -0.2194   0.03841   0.03084  -0.1273   0.7807   0.0209
  -7.750  -0.2142   0.03617   0.02818  -0.1254   0.7774   0.0215
  -7.500  -0.2036   0.03422   0.02584  -0.1238   0.7743   0.0221
  -7.250  -0.1875   0.03295   0.02443  -0.1228   0.7713   0.0229
  -7.000  -0.1695   0.03153   0.02277  -0.1218   0.7686   0.0236
  -6.750  -0.1495   0.03007   0.02101  -0.1209   0.7662   0.0246
  -6.500  -0.1278   0.02870   0.01937  -0.1200   0.7643   0.0258
  -6.250  -0.1061   0.02787   0.01846  -0.1195   0.7625   0.0274
  -6.000  -0.0890   0.02726   0.01776  -0.1182   0.7595   0.0302
  -5.750  -0.0708   0.02673   0.01718  -0.1170   0.7565   0.0331
  -5.500  -0.0517   0.02607   0.01647  -0.1159   0.7535   0.0363
  -5.250  -0.0311   0.02545   0.01580  -0.1150   0.7509   0.0411
  -5.000  -0.0092   0.02485   0.01514  -0.1143   0.7488   0.0492
  -4.750   0.0134   0.02425   0.01455  -0.1138   0.7470   0.0605
  -4.500   0.0368   0.02369   0.01402  -0.1134   0.7454   0.0779
  -4.250   0.0547   0.02340   0.01385  -0.1122   0.7427   0.1005
  -4.000   0.0697   0.02323   0.01384  -0.1106   0.7388   0.1307
  -3.750   0.0884   0.02298   0.01383  -0.1097   0.7357   0.1773
  -3.500   0.1104   0.02281   0.01369  -0.1090   0.7333   0.2297
  -3.250   0.1317   0.02236   0.01356  -0.1085   0.7312   0.2883
  -3.000   0.1543   0.02188   0.01345  -0.1080   0.7294   0.3929
  -2.750   0.1762   0.02142   0.01347  -0.1068   0.7277   0.5185
  -2.500   0.1868   0.02169   0.01411  -0.1035   0.7242   0.6129
  -2.250   0.1929   0.02237   0.01499  -0.0993   0.7198   0.6750
  -2.000   0.2075   0.02286   0.01549  -0.0965   0.7165   0.7240
  -1.750   0.2274   0.02320   0.01574  -0.0946   0.7140   0.7610
  -1.500   0.2482   0.02349   0.01593  -0.0926   0.7119   0.7906
  -1.250   0.2710   0.02371   0.01603  -0.0912   0.7103   0.8152
  -1.000   0.2744   0.02452   0.01682  -0.0872   0.7055   0.8321
  -0.750   0.2756   0.02530   0.01760  -0.0829   0.6996   0.8469
  -0.500   0.2939   0.02554   0.01775  -0.0811   0.6968   0.8594
  -0.250   0.3166   0.02565   0.01775  -0.0800   0.6947   0.8714
   0.000   0.3425   0.02566   0.01764  -0.0794   0.6930   0.8835
   0.250   0.3691   0.02562   0.01749  -0.0787   0.6917   0.8956
   0.750   0.3618   0.02731   0.01923  -0.0695   0.6779   0.9286
   1.000   0.3948   0.02726   0.01910  -0.0702   0.6763   0.9417
   1.250   0.4349   0.02721   0.01895  -0.0723   0.6751   0.9518
   1.500   0.4778   0.02710   0.01875  -0.0751   0.6741   0.9601
   2.000   0.5144   0.02915   0.02082  -0.0758   0.6603   0.9848
   2.250   0.5565   0.02903   0.02064  -0.0785   0.6589   0.9925
   2.500   0.5947   0.02888   0.02042  -0.0805   0.6577   1.0000
   3.000   0.5808   0.03089   0.02241  -0.0722   0.6419   1.0000
   3.250   0.6035   0.03119   0.02267  -0.0720   0.6383   1.0000
   3.750   0.6327   0.03273   0.02419  -0.0704   0.6254   1.0000
   4.000   0.6558   0.03309   0.02454  -0.0703   0.6213   1.0000
   5.500   0.7913   0.03505   0.02653  -0.0694   0.5914   1.0000
   6.500   0.8551   0.03781   0.02943  -0.0664   0.5616   1.0000
   6.750   0.8895   0.03709   0.02876  -0.0669   0.5598   1.0000
   7.250   0.9232   0.03821   0.02998  -0.0655   0.5447   1.0000
   8.250   0.9985   0.03974   0.03176  -0.0630   0.5140   1.0000
   8.750   1.0404   0.04012   0.03228  -0.0620   0.4980   1.0000
   9.000   1.0515   0.04119   0.03343  -0.0610   0.4863   1.0000
   9.250   1.0861   0.04014   0.03244  -0.0611   0.4811   1.0000
   9.500   1.0979   0.04116   0.03354  -0.0601   0.4687   1.0000
   9.750   1.1244   0.04085   0.03329  -0.0598   0.4598   1.0000
  10.250   1.1673   0.04115   0.03369  -0.0587   0.4364   1.0000
  10.500   1.1892   0.04126   0.03384  -0.0582   0.4239   1.0000
  10.750   1.2129   0.04121   0.03381  -0.0577   0.4108   1.0000
  11.000   1.2338   0.04141   0.03400  -0.0571   0.3965   1.0000
  11.250   1.2509   0.04197   0.03456  -0.0563   0.3811   1.0000
  11.500   1.2645   0.04286   0.03545  -0.0554   0.3652   1.0000
  11.750   1.2752   0.04405   0.03664  -0.0544   0.3493   1.0000
  12.000   1.2846   0.04538   0.03797  -0.0534   0.3335   1.0000
  12.250   1.2927   0.04687   0.03947  -0.0525   0.3177   1.0000
  12.500   1.3000   0.04850   0.04111  -0.0515   0.3024   1.0000
  12.750   1.3066   0.05022   0.04284  -0.0507   0.2875   1.0000
  13.000   1.3123   0.05207   0.04470  -0.0498   0.2730   1.0000
  13.250   1.3178   0.05401   0.04665  -0.0491   0.2590   1.0000
  13.500   1.3226   0.05605   0.04872  -0.0484   0.2455   1.0000
  13.750   1.3264   0.05823   0.05089  -0.0477   0.2324   1.0000
  14.000   1.3296   0.06053   0.05319  -0.0471   0.2196   1.0000
  14.250   1.3320   0.06304   0.05576  -0.0467   0.2072   1.0000
  14.500   1.3344   0.06559   0.05836  -0.0463   0.1954   1.0000
  14.750   1.3362   0.06825   0.06106  -0.0460   0.1842   1.0000
  15.000   1.3368   0.07106   0.06385  -0.0458   0.1737   1.0000
  15.250   1.3378   0.07399   0.06689  -0.0458   0.1631   1.0000
  15.500   1.3384   0.07701   0.06996  -0.0458   0.1534   1.0000
  15.750   1.3376   0.08020   0.07316  -0.0459   0.1446   1.0000
  16.000   1.3377   0.08345   0.07652  -0.0462   0.1355   1.0000
  16.250   1.3371   0.08679   0.07993  -0.0466   0.1275   1.0000
  16.500   1.3351   0.09036   0.08355  -0.0471   0.1200   1.0000
  16.750   1.3344   0.09387   0.08717  -0.0477   0.1125   1.0000
  17.000   1.3312   0.09770   0.09099  -0.0485   0.1063   1.0000
  17.250   1.3303   0.10137   0.09483  -0.0494   0.0994   1.0000
  17.500   1.3270   0.10534   0.09882  -0.0504   0.0940   1.0000
  17.750   1.3252   0.10924   0.10288  -0.0516   0.0880   1.0000
  18.000   1.3219   0.11330   0.10696  -0.0529   0.0833   1.0000
  18.250   1.3199   0.11730   0.11111  -0.0543   0.0781   1.0000
  18.500   1.3165   0.12145   0.11526  -0.0559   0.0741   1.0000
  18.750   1.3145   0.12553   0.11952  -0.0575   0.0695   1.0000
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