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J5012 12% (j5012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: J5012 12% (j5012-il)
Reynolds number: 50,000
Max Cl/Cd: 28.95 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-j5012-il-50000.txt
Download as CSV file: xf-j5012-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: J5012   12%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6897   0.08916   0.08163  -0.0339   1.0000   0.1528
 -10.500  -0.6930   0.08371   0.07619  -0.0349   1.0000   0.1514
 -10.250  -0.7849   0.07433   0.06671  -0.0364   1.0000   0.1380
 -10.000  -0.8024   0.07008   0.06239  -0.0343   1.0000   0.1374
  -9.750  -0.8205   0.06594   0.05810  -0.0318   1.0000   0.1369
  -9.500  -0.8359   0.06199   0.05393  -0.0289   1.0000   0.1366
  -9.250  -0.8488   0.05820   0.04986  -0.0256   1.0000   0.1366
  -9.000  -0.8599   0.05460   0.04588  -0.0219   1.0000   0.1371
  -8.750  -0.8663   0.05121   0.04205  -0.0181   1.0000   0.1380
  -8.500  -0.8615   0.04777   0.03838  -0.0155   1.0000   0.1400
  -8.250  -0.8466   0.04532   0.03593  -0.0138   1.0000   0.1457
  -8.000  -0.8438   0.04270   0.03284  -0.0103   1.0000   0.1509
  -7.750  -0.8316   0.04006   0.03001  -0.0081   1.0000   0.1570
  -7.500  -0.8197   0.03789   0.02754  -0.0055   1.0000   0.1655
  -7.250  -0.8031   0.03581   0.02543  -0.0036   1.0000   0.1765
  -7.000  -0.7868   0.03379   0.02329  -0.0016   1.0000   0.1892
  -6.750  -0.7699   0.03202   0.02147   0.0004   1.0000   0.2057
  -6.500  -0.7535   0.03033   0.01964   0.0026   1.0000   0.2262
  -6.250  -0.7349   0.02875   0.01829   0.0044   1.0000   0.2523
  -6.000  -0.7194   0.02731   0.01700   0.0069   1.0000   0.2858
  -5.750  -0.7043   0.02594   0.01597   0.0095   1.0000   0.3282
  -5.500  -0.6924   0.02472   0.01508   0.0128   1.0000   0.3818
  -5.250  -0.6816   0.02375   0.01454   0.0167   1.0000   0.4440
  -5.000  -0.6698   0.02313   0.01435   0.0208   1.0000   0.5097
  -4.750  -0.6561   0.02287   0.01441   0.0251   1.0000   0.5736
  -4.500  -0.6398   0.02293   0.01467   0.0294   1.0000   0.6324
  -4.250  -0.6177   0.02339   0.01521   0.0331   1.0000   0.6854
  -4.000  -0.5892   0.02419   0.01599   0.0362   1.0000   0.7330
  -3.750  -0.5459   0.02546   0.01712   0.0371   1.0000   0.7761
  -3.500  -0.4974   0.02663   0.01803   0.0365   1.0000   0.8159
  -3.250  -0.3909   0.02844   0.01936   0.0261   1.0000   0.8509
  -3.000  -0.3041   0.02893   0.01949   0.0168   1.0000   0.8822
  -2.750  -0.2355   0.02876   0.01906   0.0094   1.0000   0.9115
  -2.500  -0.1677   0.02824   0.01832   0.0014   1.0000   0.9391
  -2.250  -0.0941   0.02727   0.01715  -0.0085   1.0000   0.9645
  -2.000  -0.0217   0.02602   0.01574  -0.0187   1.0000   0.9891
  -1.750   0.0168   0.02506   0.01472  -0.0232   1.0000   1.0000
  -1.500   0.0197   0.02462   0.01430  -0.0209   1.0000   1.0000
  -1.250   0.0208   0.02427   0.01397  -0.0182   1.0000   1.0000
  -1.000   0.0198   0.02399   0.01371  -0.0151   1.0000   1.0000
  -0.750   0.0169   0.02379   0.01353  -0.0117   1.0000   1.0000
  -0.500   0.0123   0.02365   0.01341  -0.0079   1.0000   1.0000
  -0.250   0.0065   0.02357   0.01334  -0.0040   1.0000   1.0000
   0.000   0.0000   0.02355   0.01331   0.0000   1.0000   1.0000
   0.250  -0.0065   0.02357   0.01334   0.0040   1.0000   1.0000
   0.500  -0.0123   0.02365   0.01340   0.0079   1.0000   1.0000
   0.750  -0.0169   0.02378   0.01352   0.0117   1.0000   1.0000
   1.000  -0.0198   0.02398   0.01371   0.0151   1.0000   1.0000
   1.250  -0.0208   0.02426   0.01396   0.0182   1.0000   1.0000
   1.500  -0.0197   0.02462   0.01429   0.0208   1.0000   1.0000
   1.750  -0.0168   0.02505   0.01471   0.0232   1.0000   1.0000
   2.000   0.0213   0.02600   0.01573   0.0188   0.9892   1.0000
   2.250   0.0936   0.02726   0.01714   0.0085   0.9647   1.0000
   2.500   0.1677   0.02823   0.01831  -0.0014   0.9394   1.0000
   2.750   0.2355   0.02875   0.01905  -0.0094   0.9115   1.0000
   3.000   0.3041   0.02892   0.01948  -0.0168   0.8822   1.0000
   3.250   0.3908   0.02843   0.01937  -0.0261   0.8509   1.0000
   3.500   0.4975   0.02662   0.01803  -0.0365   0.8161   1.0000
   3.750   0.5456   0.02547   0.01713  -0.0371   0.7762   1.0000
   4.000   0.5892   0.02419   0.01599  -0.0362   0.7331   1.0000
   4.250   0.6177   0.02339   0.01521  -0.0332   0.6855   1.0000
   4.500   0.6397   0.02293   0.01467  -0.0294   0.6327   1.0000
   4.750   0.6561   0.02286   0.01440  -0.0251   0.5736   1.0000
   5.000   0.6697   0.02313   0.01434  -0.0208   0.5097   1.0000
   5.250   0.6815   0.02375   0.01453  -0.0166   0.4439   1.0000
   5.500   0.6923   0.02472   0.01508  -0.0128   0.3818   1.0000
   5.750   0.7044   0.02594   0.01597  -0.0095   0.3284   1.0000
   6.000   0.7195   0.02731   0.01699  -0.0069   0.2860   1.0000
   6.250   0.7349   0.02875   0.01829  -0.0044   0.2523   1.0000
   6.500   0.7535   0.03033   0.01965  -0.0026   0.2262   1.0000
   6.750   0.7699   0.03201   0.02146  -0.0004   0.2058   1.0000
   7.000   0.7867   0.03378   0.02328   0.0016   0.1890   1.0000
   7.250   0.8031   0.03580   0.02542   0.0036   0.1764   1.0000
   7.500   0.8195   0.03789   0.02754   0.0055   0.1654   1.0000
   7.750   0.8317   0.04005   0.03000   0.0081   0.1569   1.0000
   8.000   0.8434   0.04271   0.03286   0.0104   0.1507   1.0000
   8.250   0.8465   0.04533   0.03594   0.0138   0.1456   1.0000
   8.500   0.8613   0.04776   0.03838   0.0155   0.1400   1.0000
   8.750   0.8661   0.05122   0.04206   0.0182   0.1379   1.0000
   9.000   0.8595   0.05462   0.04591   0.0219   0.1370   1.0000
   9.250   0.8489   0.05822   0.04988   0.0256   0.1366   1.0000
   9.500   0.8341   0.06201   0.05397   0.0290   0.1364   1.0000
   9.750   0.8174   0.06598   0.05815   0.0320   0.1367   1.0000
  10.000   0.8001   0.07009   0.06240   0.0344   0.1373   1.0000
  10.250   0.7836   0.07433   0.06671   0.0364   0.1380   1.0000
  10.500   0.6367   0.09173   0.08412   0.0262   0.1625   1.0000
  10.750   0.6035   0.10251   0.09477   0.0193   0.1783   1.0000
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