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JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: JN-153 AIRFOIL (jn153-il)
Reynolds number: 1,000,000
Max Cl/Cd: 163.27 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-jn153-il-1000000.txt
Download as CSV file: xf-jn153-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: JN-153 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1782   0.09272   0.08853  -0.1013   0.4800   0.0130
  -9.250   0.1847   0.08982   0.08565  -0.1025   0.4798   0.0130
  -9.000   0.1918   0.08706   0.08291  -0.1032   0.4798   0.0131
  -8.750   0.2051   0.08540   0.08125  -0.1034   0.4796   0.0133
  -8.500   0.2143   0.08329   0.07916  -0.1041   0.4794   0.0134
  -8.250   0.2236   0.08127   0.07716  -0.1048   0.4794   0.0136
  -8.000   0.2314   0.07901   0.07492  -0.1057   0.4792   0.0137
  -7.750   0.2392   0.07678   0.07271  -0.1065   0.4790   0.0138
  -7.500   0.2467   0.07458   0.07053  -0.1073   0.4789   0.0141
  -7.250   0.2536   0.07230   0.06828  -0.1082   0.4787   0.0144
  -7.000   0.2598   0.06993   0.06593  -0.1091   0.4785   0.0147
  -6.750   0.2641   0.06730   0.06333  -0.1100   0.4784   0.0151
  -6.500   0.2666   0.06459   0.06066  -0.1109   0.4782   0.0154
  -6.250   0.2553   0.06079   0.05692  -0.1123   0.4781   0.0158
  -6.000   0.2582   0.05680   0.05296  -0.1161   0.4778   0.0158
  -5.750   0.2672   0.05244   0.04861  -0.1216   0.4774   0.0159
  -5.500   0.2748   0.04696   0.04312  -0.1285   0.4772   0.0161
  -5.250   0.2915   0.04275   0.03885  -0.1337   0.4770   0.0162
  -5.000   0.3102   0.03920   0.03520  -0.1375   0.4768   0.0163
  -4.750   0.3313   0.03641   0.03231  -0.1403   0.4764   0.0165
  -4.500   0.3545   0.03365   0.02940  -0.1427   0.4760   0.0168
  -4.250   0.3795   0.03090   0.02647  -0.1449   0.4755   0.0173
  -4.000   0.4091   0.02461   0.01942  -0.1485   0.4751   0.0192
  -3.750   0.4362   0.02355   0.01832  -0.1492   0.4748   0.0195
  -3.500   0.4695   0.01723   0.01098  -0.1510   0.4744   0.0132
  -3.250   0.4986   0.01663   0.01024  -0.1514   0.4738   0.0132
  -3.000   0.5266   0.01624   0.00977  -0.1516   0.4728   0.0133
  -2.750   0.5557   0.01588   0.00938  -0.1519   0.4724   0.0137
  -2.500   0.5852   0.01558   0.00905  -0.1522   0.4722   0.0142
  -2.250   0.6147   0.01534   0.00879  -0.1524   0.4720   0.0147
  -2.000   0.6443   0.01512   0.00853  -0.1527   0.4718   0.0152
  -1.750   0.6740   0.01490   0.00828  -0.1529   0.4715   0.0155
  -1.500   0.7037   0.01474   0.00810  -0.1532   0.4711   0.0158
  -1.250   0.7338   0.01440   0.00774  -0.1537   0.4706   0.0162
  -1.000   0.7637   0.01422   0.00756  -0.1540   0.4700   0.0167
  -0.750   0.7934   0.01411   0.00746  -0.1543   0.4694   0.0175
  -0.500   0.8230   0.01404   0.00738  -0.1546   0.4688   0.0185
  -0.250   0.8529   0.01391   0.00724  -0.1549   0.4680   0.0198
   0.000   0.8826   0.01383   0.00716  -0.1552   0.4673   0.0220
   0.250   0.9126   0.01371   0.00707  -0.1556   0.4666   0.0329
   0.500   0.9431   0.01344   0.00705  -0.1563   0.4659   0.1213
   0.750   0.9740   0.01305   0.00711  -0.1573   0.4652   0.3052
   1.000   1.0036   0.01295   0.00718  -0.1577   0.4645   0.3829
   1.250   1.0333   0.01287   0.00726  -0.1582   0.4639   0.4556
   1.500   1.0629   0.01281   0.00736  -0.1586   0.4633   0.5312
   1.750   1.0926   0.01272   0.00748  -0.1591   0.4627   0.6237
   2.000   1.1217   0.01258   0.00760  -0.1594   0.4621   0.7400
   2.250   1.1471   0.01242   0.00771  -0.1588   0.4614   0.8633
   2.500   1.1680   0.01228   0.00770  -0.1571   0.4607   1.0000
   2.750   1.1974   0.01247   0.00783  -0.1575   0.4599   1.0000
   3.000   1.2254   0.01297   0.00829  -0.1577   0.4587   1.0000
   3.250   1.2531   0.01328   0.00861  -0.1579   0.4578   1.0000
   3.500   1.2822   0.01328   0.00860  -0.1582   0.4574   1.0000
   3.750   1.3111   0.01330   0.00860  -0.1585   0.4568   1.0000
   4.000   1.3399   0.01330   0.00861  -0.1588   0.4561   1.0000
   4.250   1.3686   0.01332   0.00862  -0.1590   0.4553   1.0000
   4.500   1.3972   0.01335   0.00865  -0.1593   0.4544   1.0000
   4.750   1.4257   0.01339   0.00869  -0.1595   0.4534   1.0000
   5.000   1.4540   0.01344   0.00875  -0.1598   0.4525   1.0000
   5.250   1.4823   0.01349   0.00880  -0.1600   0.4516   1.0000
   5.500   1.5106   0.01352   0.00883  -0.1603   0.4507   1.0000
   5.750   1.5391   0.01354   0.00885  -0.1605   0.4498   1.0000
   6.000   1.5677   0.01354   0.00883  -0.1609   0.4490   1.0000
   6.250   1.5966   0.01352   0.00880  -0.1612   0.4481   1.0000
   6.500   1.6254   0.01350   0.00876  -0.1616   0.4473   1.0000
   6.750   1.6543   0.01353   0.00877  -0.1620   0.4464   1.0000
   7.000   1.6827   0.01366   0.00888  -0.1624   0.4454   1.0000
   7.250   1.7098   0.01386   0.00910  -0.1625   0.4442   1.0000
   7.500   1.7365   0.01380   0.00909  -0.1626   0.4433   1.0000
   7.750   1.7632   0.01374   0.00908  -0.1626   0.4420   1.0000
   8.000   1.7901   0.01366   0.00905  -0.1627   0.4405   1.0000
   8.250   1.8174   0.01357   0.00899  -0.1628   0.4388   1.0000
   8.500   1.8451   0.01341   0.00885  -0.1630   0.4371   1.0000
   8.750   1.8731   0.01320   0.00864  -0.1632   0.4354   1.0000
   9.000   1.9008   0.01302   0.00845  -0.1635   0.4338   1.0000
   9.250   1.9279   0.01293   0.00835  -0.1636   0.4320   1.0000
   9.500   1.9536   0.01292   0.00844  -0.1636   0.4296   1.0000
   9.750   1.9799   0.01290   0.00848  -0.1636   0.4264   1.0000
  10.000   2.0064   0.01285   0.00847  -0.1637   0.4235   1.0000
  10.250   2.0327   0.01279   0.00843  -0.1638   0.4210   1.0000
  10.500   2.0583   0.01284   0.00852  -0.1638   0.4175   1.0000
  10.750   2.0837   0.01289   0.00861  -0.1638   0.4129   1.0000
  11.000   2.1078   0.01291   0.00863  -0.1635   0.4083   1.0000
  11.250   2.1312   0.01308   0.00883  -0.1632   0.4030   1.0000
  11.500   2.1524   0.01330   0.00904  -0.1625   0.3974   1.0000
  11.750   2.1724   0.01360   0.00936  -0.1617   0.3920   1.0000
  12.000   2.1902   0.01397   0.00974  -0.1606   0.3860   1.0000
  12.250   2.2056   0.01443   0.01020  -0.1590   0.3805   1.0000
  12.500   2.2189   0.01487   0.01068  -0.1571   0.3748   1.0000
  13.000   2.2360   0.01601   0.01187  -0.1518   0.3647   1.0000
  13.250   2.2417   0.01672   0.01262  -0.1489   0.3597   1.0000
  13.500   2.2409   0.01773   0.01365  -0.1453   0.3549   1.0000
  13.750   2.2454   0.01864   0.01463  -0.1428   0.3504   1.0000
  14.000   2.2361   0.02032   0.01636  -0.1390   0.3454   1.0000
  14.250   2.2149   0.02317   0.01928  -0.1353   0.3405   1.0000
  14.500   2.1897   0.02734   0.02356  -0.1330   0.3351   1.0000
  14.750   2.0976   0.03873   0.03508  -0.1296   0.3267   1.0000
  15.000   2.0366   0.04708   0.04353  -0.1273   0.3193   1.0000
  15.250   1.9893   0.05414   0.05061  -0.1256   0.3121   1.0000
  15.500   1.9703   0.05882   0.05535  -0.1250   0.3060   1.0000
  15.750   1.9502   0.06367   0.06017  -0.1246   0.2993   1.0000
  16.000   1.9439   0.06724   0.06382  -0.1245   0.2939   1.0000
  16.250   1.9294   0.07174   0.06830  -0.1244   0.2865   1.0000
  16.500   1.9250   0.07520   0.07181  -0.1244   0.2803   1.0000
  16.750   1.9164   0.07912   0.07571  -0.1245   0.2726   1.0000
  17.000   1.9114   0.08275   0.07937  -0.1247   0.2656   1.0000
  17.250   1.9007   0.08708   0.08367  -0.1250   0.2572   1.0000
  17.500   1.9009   0.09011   0.08673  -0.1253   0.2499   1.0000
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