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JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: JN-153 AIRFOIL (jn153-il)
Reynolds number: 500,000
Max Cl/Cd: 112.57 at α=10.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-jn153-il-500000-n5.txt
Download as CSV file: xf-jn153-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.1832   0.09404   0.08881  -0.0964   0.4744   0.0152
  -9.000   0.1867   0.09094   0.08572  -0.0982   0.4744   0.0157
  -8.750   0.1882   0.08769   0.08250  -0.1001   0.4742   0.0158
  -8.250   0.2013   0.08227   0.07712  -0.1023   0.4736   0.0159
  -8.000   0.2077   0.07962   0.07448  -0.1034   0.4733   0.0159
  -7.750   0.2168   0.07756   0.07245  -0.1039   0.4729   0.0160
  -7.500   0.2300   0.07625   0.07115  -0.1038   0.4727   0.0163
  -7.250   0.2397   0.07448   0.06940  -0.1043   0.4725   0.0167
  -7.000   0.2475   0.07238   0.06733  -0.1051   0.4724   0.0171
  -6.750   0.2529   0.06992   0.06490  -0.1059   0.4723   0.0174
  -6.500   0.2576   0.06749   0.06252  -0.1068   0.4722   0.0174
  -6.250   0.2601   0.06502   0.06009  -0.1074   0.4722   0.0175
  -5.750   0.2451   0.05371   0.04886  -0.1164   0.4720   0.0129
  -5.500   0.2582   0.05087   0.04603  -0.1201   0.4718   0.0127
  -5.250   0.2741   0.04660   0.04173  -0.1262   0.4717   0.0125
  -5.000   0.2837   0.02407   0.01776  -0.1446   0.4716   0.0106
  -4.750   0.3116   0.02215   0.01550  -0.1458   0.4714   0.0107
  -4.500   0.3400   0.02099   0.01412  -0.1465   0.4712   0.0109
  -4.250   0.3688   0.02003   0.01297  -0.1471   0.4709   0.0111
  -4.000   0.3978   0.01921   0.01197  -0.1475   0.4705   0.0113
  -3.750   0.4268   0.01854   0.01115  -0.1479   0.4701   0.0116
  -3.500   0.4560   0.01797   0.01044  -0.1482   0.4698   0.0120
  -3.250   0.4852   0.01749   0.00984  -0.1485   0.4695   0.0123
  -3.000   0.5144   0.01708   0.00934  -0.1487   0.4690   0.0126
  -2.750   0.5436   0.01676   0.00895  -0.1490   0.4685   0.0129
  -2.500   0.5729   0.01645   0.00859  -0.1492   0.4680   0.0131
  -2.250   0.6021   0.01622   0.00835  -0.1496   0.4677   0.0135
  -2.000   0.6312   0.01612   0.00824  -0.1498   0.4672   0.0141
  -1.750   0.6605   0.01599   0.00810  -0.1501   0.4667   0.0148
  -1.500   0.6898   0.01587   0.00795  -0.1503   0.4661   0.0155
  -1.250   0.7192   0.01574   0.00780  -0.1506   0.4656   0.0159
  -1.000   0.7488   0.01561   0.00766  -0.1510   0.4651   0.0165
  -0.750   0.7782   0.01556   0.00760  -0.1512   0.4646   0.0173
  -0.500   0.8076   0.01551   0.00753  -0.1515   0.4641   0.0186
  -0.250   0.8370   0.01545   0.00746  -0.1518   0.4634   0.0207
   0.000   0.8664   0.01540   0.00740  -0.1521   0.4628   0.0247
   0.250   0.8959   0.01536   0.00737  -0.1524   0.4621   0.0345
   0.500   0.9256   0.01526   0.00736  -0.1528   0.4615   0.0688
   0.750   0.9562   0.01494   0.00740  -0.1537   0.4608   0.2039
   1.000   0.9866   0.01470   0.00752  -0.1546   0.4602   0.3630
   1.250   1.0161   0.01468   0.00764  -0.1550   0.4595   0.4359
   1.500   1.0455   0.01469   0.00784  -0.1555   0.4588   0.5217
   1.750   1.0742   0.01474   0.00811  -0.1558   0.4580   0.6105
   2.000   1.1022   0.01469   0.00824  -0.1559   0.4574   0.6757
   2.250   1.1294   0.01467   0.00838  -0.1558   0.4567   0.7355
   2.500   1.1548   0.01464   0.00854  -0.1553   0.4559   0.8035
   2.750   1.1739   0.01455   0.00865  -0.1533   0.4551   0.8952
   3.000   1.1996   0.01459   0.00873  -0.1529   0.4543   1.0000
   3.250   1.2277   0.01475   0.00887  -0.1530   0.4534   1.0000
   3.500   1.2557   0.01489   0.00900  -0.1532   0.4525   1.0000
   3.750   1.2838   0.01501   0.00911  -0.1534   0.4515   1.0000
   4.000   1.3118   0.01512   0.00921  -0.1536   0.4505   1.0000
   4.250   1.3399   0.01524   0.00931  -0.1538   0.4496   1.0000
   4.500   1.3680   0.01536   0.00941  -0.1540   0.4488   1.0000
   4.750   1.3962   0.01547   0.00950  -0.1542   0.4480   1.0000
   5.000   1.4244   0.01556   0.00958  -0.1544   0.4473   1.0000
   5.250   1.4527   0.01564   0.00964  -0.1547   0.4465   1.0000
   5.500   1.4811   0.01571   0.00968  -0.1550   0.4458   1.0000
   5.750   1.5095   0.01580   0.00974  -0.1553   0.4450   1.0000
   6.000   1.5362   0.01597   0.00993  -0.1553   0.4440   1.0000
   6.250   1.5612   0.01618   0.01023  -0.1551   0.4427   1.0000
   6.500   1.5865   0.01638   0.01049  -0.1550   0.4412   1.0000
   6.750   1.6122   0.01655   0.01071  -0.1549   0.4397   1.0000
   7.000   1.6381   0.01667   0.01087  -0.1549   0.4382   1.0000
   7.250   1.6644   0.01674   0.01098  -0.1549   0.4367   1.0000
   7.500   1.6910   0.01678   0.01104  -0.1549   0.4354   1.0000
   7.750   1.7177   0.01680   0.01108  -0.1550   0.4342   1.0000
   8.000   1.7444   0.01683   0.01112  -0.1551   0.4332   1.0000
   8.250   1.7710   0.01684   0.01115  -0.1551   0.4322   1.0000
   8.500   1.7941   0.01711   0.01151  -0.1548   0.4300   1.0000
   8.750   1.8167   0.01737   0.01188  -0.1543   0.4269   1.0000
   9.000   1.8410   0.01747   0.01204  -0.1541   0.4241   1.0000
   9.250   1.8661   0.01747   0.01207  -0.1539   0.4218   1.0000
   9.500   1.8917   0.01737   0.01199  -0.1538   0.4194   1.0000
   9.750   1.9134   0.01764   0.01236  -0.1533   0.4144   1.0000
  10.000   1.9376   0.01758   0.01233  -0.1530   0.4102   1.0000
  10.250   1.9609   0.01755   0.01231  -0.1526   0.4067   1.0000
  10.500   1.9818   0.01772   0.01252  -0.1518   0.4016   1.0000
  10.750   2.0014   0.01778   0.01256  -0.1508   0.3965   1.0000
  11.000   2.0162   0.01807   0.01287  -0.1491   0.3910   1.0000
  11.250   2.0264   0.01848   0.01328  -0.1467   0.3857   1.0000
  11.500   2.0341   0.01903   0.01384  -0.1440   0.3812   1.0000
  11.750   2.0408   0.01977   0.01464  -0.1415   0.3764   1.0000
  12.000   2.0403   0.02081   0.01571  -0.1382   0.3713   1.0000
  12.250   2.0352   0.02228   0.01723  -0.1349   0.3665   1.0000
  12.500   2.0179   0.02487   0.01990  -0.1315   0.3605   1.0000
  12.750   1.9707   0.03104   0.02617  -0.1286   0.3536   1.0000
  13.000   1.8880   0.04169   0.03692  -0.1260   0.3429   1.0000
  13.250   1.8376   0.04916   0.04446  -0.1242   0.3347   1.0000
  13.500   1.8179   0.05348   0.04877  -0.1232   0.3285   1.0000
  13.750   1.8001   0.05796   0.05333  -0.1226   0.3227   1.0000
  14.000   1.7924   0.06147   0.05686  -0.1222   0.3172   1.0000
  14.250   1.7926   0.06413   0.05952  -0.1220   0.3127   1.0000
  14.500   1.7848   0.06794   0.06340  -0.1219   0.3071   1.0000
  14.750   1.7851   0.07072   0.06618  -0.1218   0.3017   1.0000
  15.000   1.7833   0.07386   0.06935  -0.1218   0.2964   1.0000
  15.250   1.7810   0.07713   0.07267  -0.1219   0.2906   1.0000
  15.500   1.7849   0.07956   0.07508  -0.1220   0.2855   1.0000
  15.750   1.7852   0.08258   0.07818  -0.1222   0.2802   1.0000
  16.000   1.7833   0.08588   0.08150  -0.1224   0.2741   1.0000
  16.250   1.7845   0.08880   0.08444  -0.1226   0.2685   1.0000
  16.500   1.7840   0.09198   0.08765  -0.1230   0.2616   1.0000
  16.750   1.7845   0.09504   0.09071  -0.1233   0.2553   1.0000
  17.000   1.7818   0.09858   0.09428  -0.1237   0.2485   1.0000
  17.250   1.7818   0.10173   0.09743  -0.1242   0.2422   1.0000
  17.500   1.7817   0.10496   0.10069  -0.1247   0.2353   1.0000
  17.750   1.7776   0.10874   0.10447  -0.1253   0.2285   1.0000
  18.000   1.7770   0.11208   0.10783  -0.1259   0.2218   1.0000
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