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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 50,000
Max Cl/Cd: 13.33 at α=0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e639-il-50000.txt
Download as CSV file: xf-e639-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 639 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2815   0.11467   0.10846  -0.0254   1.0000   0.1601
  -9.250  -0.2705   0.11117   0.10501  -0.0249   1.0000   0.1680
  -9.000  -0.2856   0.11062   0.10462  -0.0271   1.0000   0.1725
  -8.750  -0.2660   0.10546   0.09952  -0.0257   1.0000   0.1792
  -8.500  -0.2730   0.10384   0.09805  -0.0266   1.0000   0.1872
  -8.250  -0.2688   0.10042   0.09475  -0.0263   1.0000   0.1928
  -8.000  -0.2707   0.09833   0.09280  -0.0260   1.0000   0.2023
  -7.750  -0.2737   0.09561   0.09026  -0.0255   1.0000   0.2083
  -7.500  -0.2800   0.09387   0.08871  -0.0242   1.0000   0.2181
  -7.250  -0.3121   0.09416   0.08934  -0.0216   1.0000   0.2195
  -7.000  -0.3445   0.09514   0.09058  -0.0150   1.0000   0.2184
  -6.750  -0.3770   0.09622   0.09185  -0.0095   1.0000   0.2165
  -6.500  -0.3596   0.09226   0.08787  -0.0204   0.9810   0.2358
  -6.250  -0.3159   0.08668   0.08228  -0.0231   0.9679   0.2630
  -6.000  -0.2964   0.08299   0.07856  -0.0301   0.9484   0.2991
  -5.500  -0.2101   0.07443   0.07004  -0.0287   0.9250   0.4239
  -5.250  -0.0738   0.06708   0.06255  -0.0242   0.9283   0.6258
  -5.000   0.1968   0.04907   0.04418  -0.0545   0.9284   0.9787
  -4.500   0.1441   0.05088   0.04591  -0.0468   0.8846   0.8369
  -4.250   0.0709   0.05256   0.04770  -0.0411   0.8619   0.7266
  -4.000   0.0160   0.05233   0.04757  -0.0390   0.8421   0.6511
  -3.750  -0.0365   0.05179   0.04712  -0.0370   0.8252   0.6033
  -3.500  -0.0273   0.04635   0.03971  -0.0724   0.8077   0.2670
  -3.250   0.0049   0.04414   0.03665  -0.0735   0.7951   0.2025
  -3.000   0.0322   0.04279   0.03453  -0.0728   0.7837   0.1726
  -2.750   0.0678   0.04056   0.03179  -0.0730   0.7752   0.1550
  -2.500   0.0877   0.03947   0.03037  -0.0715   0.7637   0.1464
  -2.250   0.1109   0.03893   0.02937  -0.0702   0.7533   0.1397
  -2.000   0.1460   0.03739   0.02751  -0.0703   0.7454   0.1363
  -1.750   0.1624   0.03731   0.02721  -0.0688   0.7347   0.1371
  -1.500   0.1927   0.03670   0.02628  -0.0684   0.7267   0.1399
  -1.250   0.2188   0.03651   0.02586  -0.0679   0.7174   0.1417
  -1.000   0.2525   0.03598   0.02530  -0.0687   0.7091   0.1467
  -0.750   0.2800   0.03586   0.02505  -0.0683   0.7013   0.1560
  -0.500   0.2958   0.03618   0.02539  -0.0669   0.6937   0.1701
  -0.250   0.3128   0.03628   0.02557  -0.0654   0.6862   0.1923
   0.000   0.3258   0.03517   0.02567  -0.0634   0.6807   0.3724
   0.250   0.4588   0.03441   0.02507  -0.0799   0.6704   1.0000
   0.500   0.4681   0.03577   0.02624  -0.0779   0.6639   1.0000
   0.750   0.4675   0.03763   0.02798  -0.0752   0.6569   1.0000
   1.000   0.4936   0.03824   0.02833  -0.0746   0.6520   1.0000
   1.250   0.4688   0.04140   0.03150  -0.0703   0.6460   1.0000
   1.500   0.4670   0.04339   0.03339  -0.0678   0.6408   1.0000
   1.750   0.5034   0.04377   0.03352  -0.0681   0.6360   1.0000
   2.000   0.4627   0.04765   0.03743  -0.0629   0.6329   1.0000
   2.250   0.4371   0.05058   0.04030  -0.0586   0.6314   1.0000
   2.500   0.4260   0.05305   0.04270  -0.0560   0.6300   1.0000
   2.750   0.4210   0.05546   0.04501  -0.0542   0.6302   1.0000
   3.000   0.4212   0.05787   0.04733  -0.0532   0.6323   1.0000
   3.250   0.4272   0.06018   0.04955  -0.0526   0.6341   1.0000
   4.750   0.3543   0.07588   0.06517  -0.0471   0.7492   1.0000
   5.000   0.3677   0.07769   0.06689  -0.0467   0.7378   1.0000
   5.250   0.4038   0.08125   0.07033  -0.0492   0.7293   1.0000
   5.500   0.4061   0.08201   0.07104  -0.0473   0.7163   1.0000
   5.750   0.4136   0.08359   0.07256  -0.0463   0.7055   1.0000
   6.000   0.4501   0.08744   0.07634  -0.0487   0.6981   1.0000
   6.250   0.4512   0.08817   0.07704  -0.0469   0.6849   1.0000
   6.500   0.4567   0.08974   0.07858  -0.0459   0.6740   1.0000
   6.750   0.4912   0.09361   0.08240  -0.0480   0.6672   1.0000
   7.000   0.4895   0.09433   0.08311  -0.0461   0.6546   1.0000
   7.250   0.4960   0.09618   0.08495  -0.0454   0.6442   1.0000
   7.500   0.5273   0.09981   0.08857  -0.0470   0.6366   1.0000
   7.750   0.5242   0.10074   0.08949  -0.0454   0.6249   1.0000
   8.000   0.5353   0.10316   0.09191  -0.0452   0.6164   1.0000
   8.250   0.5584   0.10608   0.09485  -0.0460   0.6064   1.0000
   8.500   0.5567   0.10750   0.09628  -0.0448   0.5960   1.0000
   8.750   0.5930   0.11216   0.10097  -0.0468   0.5895   1.0000
   9.000   0.5850   0.11260   0.10144  -0.0451   0.5772   1.0000
   9.250   0.5896   0.11482   0.10368  -0.0448   0.5686   1.0000
   9.500   0.6144   0.11827   0.10718  -0.0457   0.5600   1.0000
   9.750   0.6106   0.11968   0.10861  -0.0448   0.5494   1.0000
  10.000   0.6379   0.12397   0.11297  -0.0460   0.5428   1.0000
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